Base Stations For Unmanned Aerial Vehicles (UAVs)

ABSTRACT

A base station is disclosed for an unmanned aerial vehicle (UAV) that includes: an enclosure defining a window that is configured to receive the UAV to allow for entry of the UAV into the base station and exit of the UAV from the base station; a door that is movably connected to the enclosure such that the door is repositionable between a closed position and an open position; a sealing member that extends about the window and which is configured for engagement with the door so as to form a seal therewith in the closed position; and a heating system that is supported by the enclosure and which is configured to heat the door and/or the sealing member to support operation (e.g., opening and closure) of the door in a cold environment, wherein the heating system includes at least one light source and at least one heating element.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims the benefit of and priority to U.S. ProvisionalApplication No. 63/335,686, filed Apr. 27, 2022, U.S. ProvisionalApplication No. 63/356,595, filed Jun. 29, 2022, and U.S. ProvisionalApplication No. 63/356,596, filed Jun. 29, 2022, the disclosures ofwhich are hereby incorporated by reference in their entirety.

TECHNICAL FIELD

The present disclosure relates to a base station (dock) for an unmannedaerial vehicle (UAV) (e.g., a drone). More specifically, the presentdisclosure relates to a base station that includes a series ofintegrated systems, which allow for automated servicing (e.g., docking,storage, charging, operation, etc.) and accommodation of a UAV.

BACKGROUND

Known base stations for UAVs are often large, mechanically complex, andexpensive. The present disclosure addresses these deficiencies, amongothers, and provides a base station that offers improved servicing ofUAVs and significant size reductions that allow for more efficientoperation and substantial cost savings.

SUMMARY

In one aspect of the present disclosure, a base station is disclosedthat is configured for use with an unmanned aerial vehicle (UAV). Thebase station includes: an enclosure; a cradle that is configured toreceive the UAV during docking to facilitate charging of a power sourceof the UAV; and a temperature control system that is connected to thecradle and which is configured to vary temperature of the power sourceof the UAV. The cradle is movable between a retracted position, in whichthe cradle is positioned within the enclosure, and an extended position,in which the cradle is positioned externally of the enclosure tofacilitate docking with the UAV. The temperature control systemincludes: a thermoelectric conditioner (TEC) having a first end and asecond end; a first air circuit that is thermally connected to the TECand which is configured to regulate temperature of the TEC; and a secondair circuit that is thermally connected to the TEC such that the TEC islocated between the first air circuit and the second air circuit. Thesecond air circuit is configured to direct air across the cradle tothereby heat or cool the power source of the UAV when docked with thebase station.

In various embodiments, the temperature control system may be configuredto cool the power source of the UAV (e.g., when the base station and theUAV are used in hot environments) or to heat the power source of the UAV(e.g., when the base station and the UAV are used in cold environments).

In certain embodiments, the first air circuit may be configured as anopen system and the second air circuit may be configured as a closedsystem.

In certain embodiments, the TEC may be configured as a Peltier system.

In certain embodiments, the first air circuit may include: a firstplenum; a first heat sink that is connected to the first plenum and thefirst end of the TEC; and a first air circulator that is configured todirect air through the first plenum and across the first heat sink tovary air temperature within the first air circuit and thereby regulatethe temperature of the TEC.

In certain embodiments, the second air circuit may include: a secondplenum; a second heat sink that is connected to the second plenum andthe second end of the TEC; and a second air circulator that isconfigured to direct air through the second plenum and across the secondheat sink to vary air temperature within the second air circuit andthereby heat or cool the power source of the UAV when docked with thebase station.

In certain embodiments, the temperature control system may be configuredto cool the power source of the UAV when docked with the base station.

In certain embodiments, the second plenum may define an air inlet and anair outlet.

In certain embodiments, the air inlet may be configured to direct airinto the cradle and across the power source of the UAV and the airoutlet may be configured to receive the air directed across the powersource of the UAV and redirect the air across the second heat sink.

In certain embodiments, the second plenum may include a first sectionand a second section that is movable in relation to the first section.

In certain embodiments, the first section may be connected to the TECand the second section may be connected to the cradle.

In certain embodiments, the first section and the second section may beconfigured for mating engagement upon movement of the cradle into theretracted position.

In another aspect of the present disclosure, a base station is disclosedthat is configured for use with a UAV. The base station includes atemperature control system that is configured to vary temperature of theUAV. The temperature control system includes: a thermoelectricconditioner (TEC); an open air circuit that is thermally connected tothe TEC and which is configured to regulate temperature of the TEC; anda closed air circuit that is thermally connected to the TEC such thatthe TEC is located between the open air circuit and the closed aircircuit. The closed air circuit is configured to direct air across theUAV when docked with the base station.

In certain embodiments, the temperature control system may be configuredto heat or cool the UAV subject to environmental conditions.

In certain embodiments, the closed air circuit may include a firstsection and a second section that is movable in relation to the firstsection.

In certain embodiments, the base station may further include a cradlethat is configured to receive the UAV during docking to facilitatecharging of the UAV.

In certain embodiments, the cradle may be extendable from andretractable into the base station.

In certain embodiments, the first section of the closed air circuit maybe connected to the TEC and the second section of the closed air circuitmay be connected to the cradle.

In certain embodiments, the first section and the second section may beconfigured for mating engagement upon retraction of the cradle into thebase station.

In another aspect of the present disclosure, a method is disclosed forregulating the temperature of a power source in a UAV. The methodincludes: docking the UAV within a cradle of a base station; retractingthe cradle into the base station; and directing thermally conditionedair across the power source of the UAV via an air circuit that isconnected to the cradle.

In certain embodiments, the method may further include directing airacross a heat sink that is thermally connected to a thermoelectricconditioner (TEC) to treat the air prior to direction across the powersource of the UAV.

In certain embodiments, directing air across the heat sink may includecirculating the air through a plenum that is connected to the heat sink.

In certain embodiments, retracting the cradle into the base station mayinclude closing the air circuit.

In certain embodiments, closing the air circuit may include mating afirst section of the plenum with a second section of the plenum.

In certain embodiments, the first section of the plenum may be connectedto the TEC and the second section of the plenum may be connected to thecradle.

In another aspect of the present disclosure, a base station is disclosedthat is configured for use with a UAV. The base station includes: anenclosure with an outer housing that defines a roof section and an innerhousing that is connected to the outer housing; one or more heatingelements that are supported by the enclosure and which are configured toheat the roof section; one or more fiducials that are supported by theenclosure; an illumination system that is supported by the enclosure andwhich is configured to illuminate the one or more fiducials; and avisualization system that is supported by the enclosure.

In certain embodiments, the enclosure (e.g., the outer housing) maydefine one or more channels that are configured to direct water in amanner that inhibits entry into the base station.

In certain embodiments, the base station may further include one or moretemperature sensors that are in communication with the one or moreheating elements such that the one or more heating elements areactivated upon receiving a signal relayed by the one or more temperaturesensors indicating that temperature has crossed a threshold.

In certain embodiments, the one or more fiducials may include a firstfiducial and a second fiducial, each of which is supported by the roofsection.

In certain embodiments, the second fiducial may be removably connectedto the roof section.

In certain embodiments, the first fiducial may define a first surfacearea, and the second fiducial may define a second surface area that isless than the first surface area.

In certain embodiments, the first surface area may lie substantiallywithin the range of (approximately) 40 percent to (approximately) 80percent of a surface area defined by the roof section.

In certain embodiments, the second surface area may lie substantiallywithin the range of (approximately) 10 percent to (approximately) 50percent of the first surface area.

In certain embodiments, the illumination system may include one or morelight sources that are connected (secured) to the roof section and whichare configured to light the first fiducial and the second fiducial.

In certain embodiments, the illumination system may be configured tostrobe the one or more light sources according to a pattern that isrecognizable by the UAV during approach to thereby identify the basestation.

In certain embodiments, the visualization system may include a digitalimage capturing device that is configured to identify precipitation andactuate the one or more heating elements.

In certain embodiments, the base station may further include one or morestatus indicators that are supported by the enclosure (e.g., the outerhousing).

In certain embodiments, the base station may further include one or moreinternal fans to regulate temperature and/or humidity within the basestation.

In certain embodiments, the internal fan(s) may be supported by at leastone of the outer housing and the inner housing.

In another aspect of the present disclosure, a base station is disclosedthat is configured for use with a UAV. The base station includes: anenclosure; a (front) door that is movably connected to the enclosuresuch that the door is repositionable between a closed position and anopen position; and one or more actuators that extend between the doorand the enclosure. The enclosure includes an outer housing and an innerhousing that is connected to the outer housing and which defines aninternal cavity that is configured receive the UAV. Each actuatorincludes a motor assembly and a linkage assembly that extends betweenthe motor assembly and the door. The motor assembly is connected(secured) to the inner housing such that the motor assembly is locatedbetween the outer housing and the inner housing, and the linkageassembly extends through the inner housing.

In certain embodiments, the linkage assembly may include: a drive screwthat is operatively connected to the motor assembly such that actuationof the motor assembly causes rotation of the drive screw; a carrier thatis threadably engaged to the drive screw such that rotation of the drivescrew causes axial translation of the carrier; a first arm; and a secondarm.

In certain embodiments, the first arm may have a first end that ispivotably connected to the carrier and a second end, and the second armmay have a first end that is pivotably connected to the second end ofthe first arm and a second end that is pivotably connected to the door.

In certain embodiments, the base station may further include a bracketthat is fixedly connected to the door.

In certain embodiments, the bracket may be pivotably connected to thesecond end of the second arm.

In certain embodiments, the drive screw may be configured such thatrotation of the drive screw in a first direction causes advancement ofthe carrier towards the door and rotation of the drive screw in a seconddirection causes advancement of the carrier away from the door.

In certain embodiments, the drive screw may include threading defining apitch that is configured to inhibit force transmission from the door tothe carrier to thereby maintain the door in the closed position.

In another aspect of the present disclosure, a base station is disclosedthat is configured for use with an unmanned aerial vehicle (UAV). Thebase station includes: an enclosure defining an internal cavity that isconfigured to receive the UAV; a first fiducial that is supported by aroof section of the enclosure and which defines a first surface area; asecond fiducial that is supported by the roof section of the enclosureand which defines a second surface area that is less than the firstsurface area; and an illumination system that is supported by roofsection and which is configured to illuminate the first fiducial and thesecond fiducial.

In certain embodiments, the second fiducial may be configured forremovable connection to the roof section.

In certain embodiments, the first surface area may lie substantiallywithin the range of (approximately) 40 percent to (approximately) 80percent of a surface area defined by the roof section.

In certain embodiments, the second surface area may lie substantiallywithin the range of (approximately) 10 percent to (approximately) 50percent of the first surface area.

In certain embodiments, the illumination system may be configured tostrobe according to a pattern recognizable by the UAV during approach tothereby identify the base station.

In another aspect of the present disclosure, a UAV is disclosed thatincludes a power source. The power source includes: one or more powercells; one or more thermal transfer members that are thermally connectedto the one or more power cells; and a heat exchanger that is thermallyconnected to the one or more thermal transfer members such that the oneor more thermal transfer members and the heat exchanger facilitate atransfer of thermal energy between the power source and ambient air todecrease or increase temperature of the power source.

In certain embodiments, the one or more thermal transfer members mayextend between the one or more power cells and the heat exchanger.

In certain embodiments, the one or more thermal transfer members mayinclude graphite.

In certain embodiments, the one or more thermal transfer members may beunitary in construction.

In certain embodiments, the one or more power cells and the one or morethermal transfer members may correspond in number.

In certain embodiments, the one or more power cells may include aplurality of individual power cells and the one or more thermal transfermembers may include a plurality of individual thermal transfer members.

In certain embodiments, the heat exchanger may include one or morediffusers to increase surface area of the heat exchanger and thermalenergy distribution towards or away from the power source.

In certain embodiments, the one or more diffusers may extend axiallyand/or laterally along an outer surface of the heat exchanger.

In certain embodiments, the one or more diffusers may include aplurality of diffusers.

In certain embodiments, the plurality of diffusers may be configured asfins that define one or more channels therebetween.

In certain embodiments, the one or more channels may be configured todirect air flow along the heat exchanger to increase thermal energydistribution towards or away from the power source.

In another aspect of the present disclosure, a UAV is disclosed thatincludes a power source. The power source includes a heat exchanger thatis configured to transfer thermal energy between the power source andambient air to decrease or increase temperature of the power source. Theheat exchanger includes one or more diffusers to increase surface areaof the heat exchanger and thermal energy distribution towards or awayfrom the power source.

In certain embodiments, the one or more diffusers may extend axiallyand/or laterally along an outer surface of the heat exchanger.

In certain embodiments, the one or more diffusers may include aplurality of diffusers.

In certain embodiments, the plurality of diffusers may be configured asfins that define one or more channels therebetween.

In certain embodiments, the one or more channels may be configured todirect air flow along the heat exchanger to increase thermal energydistribution towards or away from the power source.

In another aspect of the present disclosure, a UAV is disclosed thatincludes: a body; one or more antennas that extend from the body; and apower source that is connected to the body. The one or more antennas arereconfigurable between an active configuration, in which the one or moreantennas extend outwardly from the body, and a passive configuration, inwhich the one or more antennas are positioned adjacent to the body. Thepower source includes one or more diffusers that extend axially and/orlaterally along an outer surface of the power source to transfer thermalenergy between the power source and ambient air to decrease or increasetemperature of the power source.

In certain embodiments, the one or more antennas may be biased towardsthe active configuration.

In certain embodiments, the one or more diffusers may include aplurality of diffusers.

In certain embodiments, the plurality of diffusers may be configured asfins that define one or more channels therebetween.

In certain embodiments, the one or more channels may be configured todirect air flow along the power source to increase thermal energydistribution towards or away from the power source.

In certain embodiments, the power source may further includes one ormore power cells and one or more thermal transfer members that arethermally connected to the one or more power cells and to the one ormore diffusers.

In certain embodiments, the one or more thermal transfer members mayinclude graphite.

In certain embodiments, the one or more thermal transfer members may beunitary in construction.

In another aspect of the present disclosure, a base station for anunmanned aerial vehicle (UAV) is disclosed that includes: an enclosure;a slide mechanism that includes openings; and a cradle.

The slide mechanism is repositionable between a retracted position andan extended position and is secured in relation (connected) to theenclosure via first mounts and second mounts. The first mounts and thesecond mounts are located between the slide mechanism and the enclosureso as to separate the slide mechanism from the enclosure and therebyreduce vibration of the slide mechanism during repositioning between theretracted position and the extended position (extension and retraction).

The cradle is connected to the slide mechanism and is configured fordocking with the UAV such that the UAV is movable into and out of theenclosure during repositioning of the slide mechanism between theretracted position and the extended position.

In certain embodiments, the enclosure may include a plurality of studsthat extend towards the slide mechanism.

In certain embodiments, each of the first mounts and the second mountsmay be configured to receive one of the plurality of studs.

In certain embodiments, the first mounts may include: a first bushing; ashank extending from the first bushing that is configured for insertioninto one of the openings in the slide mechanism; and a fastener that isconfigured for releasable connection to the shank such that the slidemechanism is secured between the first bushing and the fastener.

In certain embodiments, the first bushing may define an aperture tofacilitate connection of the first bushing to the enclosure.

In certain embodiments, the shank and the fastener may be configured forthreaded engagement.

In certain embodiments, the first bushing may include a compliantmaterial to facilitate force absorption by the first mounts and therebyreduce vibration of the slide mechanism during repositioning between theretracted position and the extended position.

In certain embodiments, the second mounts may include a second bushinghaving a non-uniform transverse cross-sectional configuration.

In certain embodiments, the second bushing may include a base portionand a stem that extends from the base portion.

In certain embodiments, the base portion may define a first transversecross-sectional dimension and the stem may define a second transversecross-sectional dimension that is less than the first transversecross-sectional dimension.

In certain embodiments, the stem may be configured for insertion intoone of the openings in the slide mechanism.

In certain embodiments, the openings in the slide mechanism may define athird transverse cross-sectional dimension that is less than the firsttransverse cross-sectional dimension and greater than the secondtransverse cross-sectional dimension, whereby the stem is receivable bythe slide mechanism such that the slide mechanism is movable in relationto the second mounts in two degrees-of-freedom that are oriented ingenerally orthogonal relation.

In certain embodiments, the second mounts may further include a fastenerthat is configured to secure the second bushing in relation to theenclosure.

In another aspect of the present disclosure, a base station for anunmanned aerial vehicle (UAV) is disclosed that includes: an enclosurehaving a plurality of studs that extend upwardly therefrom; a slidemechanism that includes openings; and a cradle.

The slide mechanism is repositionable between a retracted position andan extended position and is indirectly connected to the enclosure viafirst mounts and second mounts. The first mounts include a firstthreaded interface that is configured for connection to one of theplurality of studs and a second threaded interface that is separatedfrom the first threaded interface by a compliant material. The secondmounts include: a base portion that defines a first transversecross-sectional dimension; a stem that extends from the base portion andwhich defines a second transverse cross-sectional dimension that is lessthan the first transverse cross-sectional dimension; and a channel thatextends through the base portion and the stem and which is configured toreceive one of the plurality of studs.

The cradle is connected to the slide mechanism and is configured fordocking with the UAV such that the UAV is movable into and out of theenclosure via the slide mechanism.

In certain embodiments, the first mounts and the second mounts may belocated between the enclosure and the slide mechanism such that theenclosure and the slide mechanism are physically separated by the firstmounts and the second mounts.

In certain embodiments, the second threaded interface may include ashank that is configured for insertion into one of the openings in theslide mechanism and which is configured for connection to a fastener tothereby secure the first mounts and the slide mechanism to theenclosure.

In certain embodiments, the stem may be configured for insertion intoone of the openings in the slide mechanism, which defines a thirdtransverse cross-sectional dimension that is less than the firsttransverse cross-sectional dimension and greater than the secondtransverse cross-sectional dimension such that a lateral gap is definedbetween the stem and the opening in the slide mechanism to allow forpredetermined lateral movement of the slide mechanism within theenclosure to inhibit lateral over-travel of the slide mechanism.

In certain embodiments, the second mounts may further include a fastenerthat is configured for releasable connection to the stud received by thechannel such that an axial gap is defined between the fastener and thebase portion to allow for predetermined axial movement of the slidemechanism within the enclosure to inhibit axial over-travel of the slidemechanism.

In another aspect of the present disclosure, a base station for anunmanned aerial vehicle (UAV) is disclosed that includes: an enclosure;a slide mechanism that includes openings and which is retractable andextendable in relation to the housing to facilitate movement of the UAVinto and out of the enclosure; first mounts that are configured forinsertion into the slide mechanism such that the first mounts arelocated between the slide mechanism and the enclosure; and second mountsthat are configured for insertion into the slide mechanism such that thesecond mounts are located between the slide mechanism and the enclosure,wherein the first mounts and the second mounts include non-identicalconfigurations.

In certain embodiments, the first mounts may be fixed in relation to theslide mechanism.

In certain embodiments, the second mounts may be configured tofacilitate relative movement between the second mounts and the slidemechanism.

In certain embodiments, the second mounts may include a steppedconfiguration.

In certain embodiments, the second mounts may include a base portiondefining a first transverse cross-sectional dimension and a stem thatextends from the base portion and which defines a second transversecross-sectional dimension that is less than the first transversecross-sectional dimension.

In certain embodiments, the stem may be configured for insertion intoone of the openings in the slide mechanism so as to define lateral andaxial gaps allowing for predetermined lateral and axial movement of theslide mechanism within the enclosure in two degrees-of-freedom toinhibit over-travel of the slide mechanism and unintended contactbetween the slide mechanism and internal components of the base station.

In another aspect of the present disclosure, a method of assembling abase station for an unmanned aerial vehicle (UAV) is disclosed. Themethod includes: connecting first mounts to an enclosure of the basestation; connecting second mounts to the enclosure, wherein the firstmounts include a first configuration, and the second mounts include asecond, different configuration; connecting a slide mechanism to thefirst mounts and the second mounts such that the first mounts and thesecond mounts are located between the slide mechanism and the enclosureto thereby separate the slide mechanism from the enclosure and reducevibration of the slide mechanism during extension and retraction; andconnecting a cradle configured for docking with the UAV to the slidemechanism such that the UAV is movable into and out of the enclosureduring extension and retraction of the slide mechanism.

In certain embodiments, connecting the first mounts to the enclosure mayinclude inserting first studs extending from the enclosure intoapertures defined by the first mounts.

In certain embodiments, inserting the first studs into the aperturesdefined by the first mounts may include threadably connecting the firststuds to first bushings of the first mounts such that the first studsextend partially into the first bushings.

In certain embodiments, connecting the second mounts to the enclosuremay include inserting second studs extending from the enclosure intochannels defined by second bushings of the second mounts such that thesecond studs extend through the second mounts.

In certain embodiments, connecting the slide mechanism to the firstmounts may include inserting shanks extending from the first bushingsinto openings in the slide mechanism.

In certain embodiments, connecting the slide mechanism to the secondmounts may include inserting the second bushings into openings in theslide mechanism.

In certain embodiments, inserting the second bushings into the openingsin the slide mechanism may include positioning base portions of thesecond bushings between the enclosure and the slide mechanism andinserting stems extending from the base portions into the openings inthe slide mechanism such that the slide mechanism is movable in relationto the second mounts in two degrees-of-freedom oriented in generallyorthogonal relation.

In certain embodiments, connecting the slide mechanism to the firstmounts may include threadably connecting first fasteners to the shanksextending from the first bushings.

In certain embodiments, connecting the slide mechanism to the secondmounts may include threadably connecting second fasteners to the secondstuds extending through the second bushings.

In certain embodiments, connecting the slide mechanism to the secondmounts may include forming radial gaps between the stems and theopenings in the slide mechanism and forming axial gaps between the baseportions and the second fasteners.

In another aspect of the present disclosure, a base station for anunmanned aerial vehicle (UAV) is disclosed that includes: an enclosuredefining an internal cavity that is configured to receive the UAV; a(front) door that is movably connected to the enclosure; actuators thatextend between the door and the enclosure to facilitate opening andclosure of the door; a cradle that is configured to receive the UAV; andengagement members that are connected (secured) to the actuators andwhich are configured for contact with propeller assemblies on the UAV tofacilitate folding of the propeller assemblies during movement of theUAV into the enclosure.

The cradle is movable in relation to the enclosure such that the cradleis repositionable between a retracted position and an extended positionto facilitate movement of the UAV into and out of the enclosure.

In certain embodiments, the engagement members may include a compliantmaterial to inhibit unseating of the UAV from the cradle upon contactbetween the engagement members and the propeller assemblies.

In certain embodiments, the engagement members may include mountingbrackets that are configured for connection to the actuators.

In certain embodiments, the actuators may include a first actuator and asecond actuator that is spaced laterally from the first actuator along awidth of the enclosure.

In certain embodiments, the engagement members may include a firstengagement member that is connected to the first actuator and a secondengagement member that is connected to the second actuator such that thesecond engagement member is spaced laterally from the first engagementmember along the width of the enclosure.

In another aspect of the present disclosure, a method of docking anunmanned aerial vehicle (UAV) within a base station is disclosed thatincludes: opening a (front) door of the base station; performing a firststage retraction of the UAV into the base station; partially foldingrear propeller assemblies on the UAV via rotation of the rear propellerassemblies into contact with engagement members on the base station;performing a second stage retraction of the UAV into the base station;completely folding the rear propeller assemblies via rotation of therear propeller assemblies into contact with the engagement members;performing a third stage retraction of the UAV into the base station;partially folding front propeller assemblies on the UAV via rotation ofthe front propeller assemblies into contact with the engagement members;and completely folding the front propeller assemblies.

In certain embodiments, performing the second stage retraction of theUAV may include folding an antenna on the UAV via contact with the door.

In certain embodiments, partially folding the rear propeller assembliesmay include rotating a first rear propeller assembly in a firstdirection and rotating a second rear propeller assembly in a seconddirection, which is opposite to the first direction.

In certain embodiments, completely folding the rear propeller assembliesmay include rotating the first rear propeller assembly in the seconddirection and rotating the second rear propeller assembly in the firstdirection.

In certain embodiments, completely folding the rear propeller assembliesmay include positioning the rear propeller assemblies such that they areoriented towards the front propeller assemblies.

In certain embodiments, the method may further include partially closingthe door to facilitate contact between the engagement members and thefront propeller assemblies.

In certain embodiments, partially folding the front propeller assembliesmay include actively rotating a first front propeller assembly in thesecond direction and actively rotating a second front propeller assemblyin the first direction.

In certain embodiments, partially folding the front propeller assembliesmay further include passively rotating the first front propellerassembly in the first direction and passively rotating the second frontpropeller assembly in the second direction.

In certain embodiments, passively rotating the first front propellerassembly and passively rotating the second front propeller assembly mayinclude performing a fourth stage retraction of the UAV into the basestation.

In certain embodiments, partially folding the front propeller assembliesmay include positioning the front propeller assemblies such that theyare oriented away from the rear propeller assemblies.

In certain embodiments, completely folding the front propellerassemblies may include rotating the first front propeller assembly inthe first direction and rotating the second front propeller assembly inthe second direction.

In certain embodiments, completely folding the front propellerassemblies may include actively rotating the front propeller assembliessuch that they are oriented towards the rear propeller assemblies.

In another aspect of the present disclosure, a method of docking anunmanned aerial vehicle (UAV) within a base station is disclosed thatincludes: folding rear propeller assemblies on the UAV via rotation ofthe rear propeller assemblies into contact with engagement members onthe base station; retracting the UAV into the base station; and foldingfront propeller assemblies on the UAV via rotation of the frontpropeller assemblies into contact with the engagement members.

In certain embodiments, the method may further include adjusting aposition of a (front) door of the base station to facilitate contactbetween the engagement members and the rear propeller assemblies andcontact between the engagement members and the front propellerassemblies.

In certain embodiments, folding the rear propeller assemblies andfolding the front propeller assemblies may include rotating the rearpropeller assemblies and rotating the front propeller assemblies intobumpers supported by actuators connected to the door of the basestation, the actuators being configured to facilitate opening andclosure of the door.

In certain embodiments, folding the rear propeller assemblies andfolding the front propeller assemblies may include rotating the rearpropeller assemblies and rotating the front propeller assemblies intobumpers supported by the door.

In another aspect of the present disclosure, a base station for anunmanned aerial vehicle (UAV) is disclosed. The base station includes:an enclosure; a slide mechanism that is connected to the enclosure andwhich is repositionable between a retracted position and an extendedposition; a cradle that is connected to the slide mechanism and which isconfigured for docking with the UAV such that the UAV is movable intoand out of the enclosure during repositioning of the slide mechanismbetween the retracted position and the extended position; and a charginghub that is connected to the slide mechanism and which is configured forelectrical connection to a power source of the UAV to charge the powersource.

In certain embodiments, the slide mechanism may include a stationaryslide member that is fixedly connected to the enclosure and a movableslide member that is slidable in relation to the stationary slidemember.

In certain embodiments, the charging hub may be connected to thestationary slide member.

In certain embodiments, the charging hub may extend into the cradle whenthe slide mechanism is in the retracted position.

In certain embodiments, the charging hub may include a charging memberthat is configured for electrical connection to the power source of theUAV.

In certain embodiments, the cradle may define an opening that isconfigured to receive the charging member such that the charging membermoves into and out of the cradle during repositioning of the slidemechanism between the retracted position and the extended position.

In certain embodiments, the charging hub may include: a base that isconnected to the slide mechanism; an alignment bracket that is (movably)supported by the base; and a charging member that is connected to thealignment bracket and which is configured for electrical connection tothe power source.

In certain embodiments, the charging member may be connected to thealignment bracket such that the charging member and the alignmentbracket are movable in unison along an axis of movement.

In certain embodiments, the alignment bracket may include an anchor thatextends into a corresponding opening in the charging member to inhibitrelative movement between the alignment bracket and the charging member.

In certain embodiments, the base may be fixedly connected to the slidemechanism.

In certain embodiments, the base may define a cavity that is configuredto receive the alignment bracket such that the alignment bracket ismovable through the cavity during repositioning between a normalposition and a deflected position.

In certain embodiments, the base may include a base wall defining thecavity.

In certain embodiments, the base wall may define an opening that isconfigured to receive the alignment bracket to facilitate assembly ofthe charging hub.

In certain embodiments, the base wall may be configured to support thealignment bracket during repositioning between the normal position andthe deflected position.

In certain embodiments, the base wall may define a chamfered surfacethat is configured for engagement with the alignment bracket tofacilitate repositioning of the alignment bracket between the normalposition and the deflected position.

In certain embodiments, the charging hub may further include a biasingmember that is located within the cavity.

In certain embodiments, the biasing member may be configured to bias thealignment bracket towards the normal position.

In certain embodiments, the biasing member may include a first end thatis in engagement with the base and a second end that is in engagementwith the alignment bracket.

In certain embodiments, the alignment bracket may include an alignmentmember that is configured for insertion into a receptacle defined by thepower source of the UAV.

In certain embodiments, the alignment member may extend axially forwardof the charging member along the axis of movement.

In certain embodiments, the alignment member may be vertically offsetfrom the biasing member.

In certain embodiments, the charging hub may further include a cap thatis removably connected to the base.

In certain embodiments, the cap may overlie the charging member toinhibit rotation of the charging member and the alignment bracket inrelation to the base.

In another aspect of the present disclosure, a charging hub is disclosedfor a base station that is configured for use with an unmanned aerialvehicle (UAV). The charging hub includes: a base; an alignment bracketthat is movably supported by the base such that the alignment bracket isrepositionable between a normal position and a deflected position; abiasing member that is positioned between the base and the alignmentbracket and which is configured to bias the alignment bracket towardsthe normal position; a charging member that is connected to thealignment bracket such that the charging member moves contemporaneouslywith the alignment bracket during repositioning of the alignment bracketbetween the normal position and the deflected position; and a cap thatis removably connected to the base such that the cap overlies thecharging member to inhibit rotation of the charging member and thealignment bracket in relation to the base.

In certain embodiments, the biasing member may include a first end thatis in engagement with the base and a second end that is in engagementwith the alignment bracket.

In certain embodiments, the alignment bracket may include an anchor thatextends into a corresponding opening in the charging member to inhibitrelative movement between the alignment bracket and the charging member.

In certain embodiments, the base may define a cavity that is configuredto receive the alignment bracket such that the alignment bracket ismovable through the cavity during repositioning between the normalposition and the deflected position.

In certain embodiments, the base may define an opening that isconfigured to receive the alignment bracket to facilitate assembly ofthe charging hub.

In certain embodiments, the base may include a base wall defining thecavity.

In certain embodiments, the base wall may be configured to support thealignment bracket during repositioning between the normal position andthe deflected position.

In certain embodiments, the base wall may define a chamfered surfacethat is configured for engagement with the alignment bracket tofacilitate repositioning of the alignment bracket between the normalposition and the deflected position.

In certain embodiments, the alignment bracket may include an alignmentmember that is configured for insertion into a receptacle defined by apower source of the UAV.

In certain embodiments, the alignment member may extend axially forwardof the charging member and may be vertically offset from the biasingmember.

In another aspect of the present disclosure, a method of using a basestation to charge an unmanned aerial vehicle (UAV) is disclosed. Themethod includes: docking the UAV with a cradle of the base station;retracting the cradle into an enclosure of the base station via a slidemechanism; and electrically connecting a power source of the UAV to acharging hub connected to the slide mechanism to thereby charge thepower source.

In certain embodiments, docking the UAV with the cradle may includeguiding the power source into a chamber defined by the cradle viacontact between the UAV and tapered sidewalls of the cradle.

In certain embodiments, retracting the cradle may include repositioningthe slide mechanism from an extended position into a retracted position.

In certain embodiments, repositioning the slide mechanism from theextended position into the retracted position may include telescopicallyrepositioning a movable slide member in relation to a stationary slidemember.

In certain embodiments, the charging hub may be connected to thestationary slide member.

In certain embodiments, electrically connecting the power source of theUAV to the charging hub may include inserting a charging member into thepower source.

In certain embodiments, retracting the cradle may include aligning afirst electrical connector on the charging hub with an opening on thepower source to thereby facilitate engagement of the first electricalconnector with a second electrical connector on the power source.

In certain embodiments, aligning the first electrical connector with theopening on the power source may include inserting an alignment bracketon the charging hub into a receptacle defined by the power source.

In certain embodiments, retracting the cradle may include inserting thealignment bracket into the receptacle.

In certain embodiments, inserting the alignment bracket into thereceptacle may include repositioning the alignment bracket from a normalposition into a deflected position via movement of the alignment bracketin relation to a base of the charging hub along an axis of movement.

In certain embodiments, the method may further include repositioning thealignment bracket from the normal position into the deflected position,wherein the charging member is connected to the alignment bracket suchthat the charging member and the alignment bracket move in unison.

In certain embodiments, repositioning the alignment bracket from thenormal position into the deflected position may include compressing abiasing member that is located between the alignment bracket and a baseof the charging hub, wherein the biasing member is configured to biasthe alignment bracket towards the normal position.

In certain embodiments, repositioning the alignment bracket from thenormal position into the deflected position may include increasing apreloaded force (e.g., a biasing force) applied to the alignmentbracket.

In certain embodiments, inserting the alignment bracket into thereceptacle may include inserting an alignment member on the alignmentbracket into the receptacle.

In certain embodiments, the alignment member may extend axially forwardof the first electrical connector along the axis of movement.

In certain embodiments, repositioning the alignment bracket from thenormal position into the deflected position may include inhibitingrotation of the alignment bracket and the first electrical connector inrelation to the base via a cap that is removably connected to the base.

In another aspect of the present disclosure, a method of using a basestation to charge an unmanned aerial vehicle (UAV) is disclosed. Themethod includes: docking the UAV with the base station; retracting theUAV towards a charging hub of the base station; inserting an alignmentmember carried by an alignment bracket on the charging hub into areceptacle on a power source of the UAV; inserting a charging member onthe charging hub into an opening on the power source; increasing apreloaded force applied to the alignment bracket by a biasing memberpositioned within a base of the charging hub, wherein the biasing memberis vertically offset from the alignment member; and inhibiting rotationof the alignment bracket in relation to the base via a cap overlying thecharging member.

In certain embodiments, increasing the preloaded force may includedisplacing the alignment bracket and the charging member.

In certain embodiments, displacing the alignment bracket and thecharging member may include compressing the biasing member between thealignment bracket and the base.

In certain embodiments, displacing the alignment bracket and thecharging member may include moving the alignment bracket and thecharging member in unison.

In certain embodiments, displacing the alignment bracket and thecharging member may include moving the charging member axially within achannel defined by the cap.

In another aspect of the present disclosure, a method of using a basestation to charge an unmanned aerial vehicle (UAV) is disclosed. Themethod includes: docking the UAV with the base station; retracting theUAV towards a charging hub of the base station so as to insert analignment bracket on the charging hub into a receptacle defined by apower source of the UAV and thereby align a first electrical connectoron the charging hub with a second electrical connector on the powersource; and engaging the first electrical connector and the secondelectrical connector to thereby establish an electrical connectionbetween the base station and the UAV and charge the power source.

In certain embodiments, retracting the UAV towards the charging hub mayinclude compressing a biasing member positioned between the alignmentbracket and a base of the charging hub supporting the alignment bracket.

In certain embodiments, compressing the biasing member may includecompressing the biasing member within a cavity defined by the base.

In certain embodiments, retracting the UAV towards the charging hub mayinclude displacing the alignment bracket to thereby compress the biasingmember.

In certain embodiments, displacing the alignment bracket may includecausing corresponding displacement of a charging member supporting thefirst electrical connector and connected to the alignment bracket suchthat the alignment bracket and the charging member move in unison.

In another aspect of the present disclosure, a base station is disclosedfor an unmanned aerial vehicle (UAV). The base station includes: anenclosure that is configured to receive the UAV and which includes afront end having a front door and a rear end having a rear door; a slidemechanism that is connected to the enclosure; a cradle that isconfigured for docking with the UAV and which is connected to the slidemechanism such that the UAV is movable into and out of the enclosureduring repositioning of the cradle between a retracted position and anextended position; a first electronics module that is removablyconnected to the enclosure adjacent to the rear door; a secondelectronics module that is removably connected to a roof section of theenclosure; and a third electronics module that is removably connected tothe slide mechanism, whereby the first electronics module, the secondelectronics module, and the third electronics module are individuallyremovable from the base station.

In certain embodiments, the first electronics module may include a mainheat sink and an auxiliary heat sink.

In certain embodiments, the auxiliary heat sink may be connected to themain heat sink such that the main heat sink defines a plurality of sidewalls collectively describing a perimeter of the first electronicsmodule and the auxiliary heat sink defines an end wall of the firstelectronics module.

In certain embodiments, the auxiliary heat sink may include one or morediffusers that are configured to increase thermal energy distribution(e.g., of the auxiliary heat sink).

In certain embodiments, the first electronics module may furtherinclude: a logic board that is supported by the main heat sink such thatthe logic board is located between the main heat sink and the auxiliaryheat sink; a first printed circuit board assembly (PCBA) that issupported by the main heat sink; and an interface member that is locatedbetween the main heat sink and the first PCBA.

In certain embodiments, the first electronics module may be configuredto facilitate data processing and control of the base station. Forexample, in certain embodiments, the first PCBA may include a processorthat is configured to facilitate data processing and control of the basestation.

In certain embodiments, the main heat sink may define a cavity that isconfigured to receive the logic board.

In certain embodiments, the interface member may include at least onethermally conductive section that is configured to facilitate thermalenergy transfer between the first PCBA and the main heat sink and atleast one electrically conductive section that is configured toelectrically ground the first PCBA.

In certain embodiments, the at least one electrically conductive sectionmay include an adhesive to connect the first PCBA to the main heat sink.

In certain embodiments, the base station may further include an aircirculation module that is connected to the enclosure adjacent to therear door.

In certain embodiments, the air circulation module may be positionedabout the first electronics module to facilitate cooling thereof.

In certain embodiments, the enclosure may include a frame that definesan outer surface and an inner surface.

In certain embodiments, the first electronics module may be connected tothe outer surface of the frame and the air circulation module may beconnected to the inner surface of the frame such that the frame islocated between the first electronics module and the air circulationmodule, whereby the first electronics module is removable from the basestation separately from the air circulation module.

In certain embodiments, the air circulation module may include ductingthat is configured to direct air across the first electronics module anda fan that is supported by the ducting.

In certain embodiments, the rear door may include a non-metallic frameand a metallic panel that is connected to the non-metallic frame.

In certain embodiments, the metallic panel may be positioned incorrespondence with the first electronics module so as to create aFaraday cage for the first electronics module and thereby reduceelectromagnetic emissions from the base station.

In certain embodiments, the rear door may further include a sealingmember that extends about the metallic panel and which is configured forengagement with the enclosure.

In certain embodiments, the second electronics module may be configuredto control opening and closure of the front door.

In certain embodiments, the second electronics module may include: anaccess panel that is removably connected to the roof section of theenclosure; a second PCBA that is connected to the access panel; and afan that is connected to the access panel.

In certain embodiments, the access panel may be removably connected toan inner surface of the roof section via a plurality of mechanicalfasteners such that the second electronics module is accessible fromwithin the enclosure.

In certain embodiments, the plurality of mechanical fasteners may beconfigured as thumb screws to allow for toolless connection anddisconnection of the access panel.

In certain embodiments, the third electronics module may be configuredto facilitate and control repositioning of the cradle between theretracted position and the extended position. For example, in certainembodiments, the third electronics module may be configured to controlthe slide mechanism.

In certain embodiments, the third electronics module may include a thirdPCBA that is removably connected to the slide mechanism via a pluralityof mechanical fasteners such that the third electronics module isaccessible from within the enclosure upon removal of the UAV.

In certain embodiments, the slide mechanism may include a stationaryslide member that is connected to the enclosure and a movable slidemember that is slidable in relation to the stationary slide member.

In certain embodiments, the third PCBA may be removably connected to thestationary slide member.

In another aspect of the present disclosure, a base station is disclosedfor an unmanned aerial vehicle (UAV). The base station includes: anenclosure defining a window that is configured to receive the UAV toallow for entry of the UAV into the base station and exit of the UAVfrom the base station; a door that is movably connected to the enclosuresuch that the door is repositionable between a closed position and anopen position; a sealing member that extends about the window and whichis configured for engagement with the door so as to form a sealtherewith when the door is in the closed position; and a heating systemthat is supported by the enclosure and which is configured to heat thedoor and/or the sealing member to support operation (e.g., opening andclosure) of the door in a cold environment.

In certain embodiments, the heating system may include at least onelight source and at least one heating element.

In certain embodiments, the at least one light source may be configuredto identify a status of the base station.

In certain embodiments, the at least one light source may be supportedon an outer surface of the enclosure and the at least one heatingelement may be supported on an inner surface of the enclosure.

In certain embodiments, the base station may further include a thermalinterface material that is located between the enclosure and the atleast one heating element.

In certain embodiments, the heating system may further include at leastone temperature sensor that is supported by the enclosure.

In certain embodiments, the door may include a thermally conductivemember to further facilitate heating of the door.

In certain embodiments, the thermally conductive member may be embeddedwithin the door.

In certain embodiments, the sealing member may include a thermallyconductive member to further facilitate heating of the sealing member.

In certain embodiments, the thermally conductive member may be embeddedwithin the sealing member.

In certain embodiments, the base station may further include at leastone additional heating element that is supported by a roof section ofthe enclosure.

In another aspect of the present disclosure, a docking system isdisclosed for an unmanned aerial vehicle (UAV). The docking systemincludes a base station that is configured to receive the UAV and apedestal that is configured to support the base station in an elevatedposition. The pedestal defines an interior space that is configured incorrespondence with an outer contour of the base station such that thebase station is positionable within the pedestal to protect the basestation during nonuse.

In certain embodiments, the pedestal may be unitary in construction.

In certain embodiments, the pedestal may include: an upper wall having anon-linear configuration; first and second side walls extending from theupper wall, wherein each of the first and second side walls have agenerally linear configuration; and first and second base wallsextending laterally inward from the first and second side walls,respectively, wherein each of the first and second base walls have agenerally linear configuration.

In certain embodiments, the upper wall may include: a first segment thatextends laterally inward from the first side wall; a second segment thatextends laterally inward from the second side wall; a third segment thatextends in generally parallel relation to the first segment and thesecond segment; a fourth segment that extends between the first segmentand the third segment; and a fifth segment that extends between thesecond segment and the third segment.

In certain embodiments, the first segment and the second segment may bevertically aligned.

In certain embodiments, the third segment may be vertically offset fromthe first segment and the second segment so as to define a well.

In certain embodiments, the first side wall may be configured so as todefine a first acute angle with a first reference axis oriented ingenerally orthogonal relation to the first base wall and the second sidewall may be configured so as to define a second acute angle with asecond reference axis oriented in generally orthogonal relation to thesecond base wall.

In certain embodiments, the well may be configured in correspondencewith at least one antenna on the base station to create verticalclearance for the at least one antenna when the base station ispositioned within the pedestal.

In certain embodiments, the base station may include a pair of antennas.

In certain embodiments, the fourth segment and the fifth segment mayrespectively subtend generally identical obtuse angles with the firstsegment and the second segment such that the well extends into a spacedefined between the pair of antennas when the base station is positionedwithin the pedestal.

In another aspect of the present disclosure, a base station is disclosedfor an unmanned aerial vehicle (UAV). The base station includes: anenclosure; a slide mechanism that is connected to the enclosure andwhich is repositionable between a retracted position and an extendedposition; and a cradle that is connected to the slide mechanism andwhich defines a chamber that is configured to receive the UAV such thatthe UAV is movable into and out of the enclosure during repositioning ofthe slide mechanism between the retracted position and the extendedposition. The cradle includes: an upper shell; a lower shell that isconnected to the upper shell; and at least one thermal insulator that islocated between the upper shell and the lower shell.

In certain embodiments, the cradle may define an airflow channel thatextends about the chamber and which is configured to facilitate aircirculation within the cradle.

In certain embodiments, the cradle may further define an air inlet(vent) and an air outlet (vent) that are in communication with theairflow channel and which are configured to direct air flow across thechamber to thereby heat or cool a power source of the UAV when the UAVis docked within the cradle.

In certain embodiments, the cradle may include a rear end that defineslead-ins which are configured for engagement with the enclosure duringretraction of the cradle to facilitate entry of the cradle into theenclosure.

In certain embodiments, the upper shell may define an angled guidesurface that is configured for engagement with the UAV to thereby directthe UAV into the chamber and facilitate proper docking of the UAV withinthe cradle.

In certain embodiments, the upper shell and the lower shell may eachinclude a non-metallic material.

In certain embodiments, the at least one thermal insulator may includean insulative foam.

In certain embodiments, the airflow channel may be defined by the atleast one thermal insulator.

In certain embodiments, the airflow channel may include a discontinuousconfiguration.

In certain embodiments, the airflow channel may include a first channelportion and a second channel portion.

In certain embodiments, the first channel portion and the second channelportion may be separated by a nose section of the cradle.

In certain embodiments, the first channel portion may be incommunication with the air inlet and the second channel portion may bein communication with the air outlet.

In another aspect of the present disclosure, a base station is disclosedfor an unmanned aerial vehicle (UAV). The base station includes: anenclosure that is configured to receive the UAV; a door that is movablyconnected to the enclosure such that the door is repositionable betweena closed position and an open position; a primary heating system that isassociated with a roof section of the enclosure; and a secondary heatingsystem that is associated with the door.

In certain embodiments, the secondary heating system may include anexterior light source and an interior heating element.

In certain embodiments, the primary heating system and/or the secondaryheating system may be configured for automatic activation upon receivingan activation signal.

In certain embodiments, the base station may further include atemperature sensor that is configured to relay the activation signal tothe primary heating system and/or the secondary heating system upondetecting a threshold temperature.

In certain embodiments, the base station may further include avisualization system that is supported by the enclosure and which isconfigured to visually inspect environmental conditions.

In certain embodiments, the visualization system may be configured torelay the activation signal to the primary heating system and/or thesecondary heating system.

In another aspect of the present disclosure, a method is disclosed forheating a base station for an unmanned aerial vehicle (UAV). The methodincludes activating a primary heating system that is associated with aroof section of the base station to expose at least one fiducial that issupported by the roof section and thereby facilitate visualidentification of the base station by the UAV and/or guidance of the UAVduring landing and docking with the base station.

In certain embodiments, the method may further include activating asecondary heating system that is associated with a door of the basestation to facilitate opening and closure thereof.

In certain embodiments, activating the secondary heating system mayinclude activating at least one thermally conductive member, wherein theat least one thermally conductive member is connected to the door and/ora sealing member that is configured for engagement with the door.

In certain embodiments, activating the secondary heating system mayinclude activating an exterior light source and activating an interiorheating element.

In certain embodiments, activating the primary heating system andactivating the secondary heating system may include automaticallyactivating the primary heating system and automatically activating thesecondary heating system upon receiving an activation signal from atleast one of: a temperature sensor on the base station that isconfigured to detect a threshold temperature; a visualization system onthe base station that is configured to visually inspect environmentalconditions; and a weather station that is wirelessly connected to thebase station.

In another aspect of the present disclosure, a docking system isdisclosed for an unmanned aerial vehicle (UAV). The docking systemincludes a base station that is configured to receive the UAV and apedestal that is configured to receive and support the base station suchthat the docking system is reconfigurable between a nestedconfiguration, in which the base station is positioned within aninterior space defined by the pedestal, and a stacked configuration, inwhich the base station is supported by the pedestal in an elevatedposition.

In certain embodiments, the pedestal may be configured to createclearance with the base station about an entire periphery thereof so asto inhibit contact between the pedestal and the base station in thenested configuration.

In certain embodiments, the interior space may be configured incorrespondence with an outer contour of the base station.

In certain embodiments, the base station may include a pair of antennas.

In certain embodiments, the pedestal may define a well that isconfigured for positioning between the pair of antennas when the dockingsystem is in the nested configuration.

In certain embodiments, the pedestal may include a plurality ofadjustable footings that are configured for removable connectionthereto.

In another aspect of the present disclosure, a method of using a dockingsystem for an unmanned aerial vehicle (UAV) is disclosed. The methodincludes: storing a base station for the UAV within an interior spacedefined by a pedestal during nonuse of the base station; removing thebase station from the interior space defined by the pedestal; andsupporting the base station on the pedestal in an elevated position.

In certain embodiments, the method may further include adjusting atleast one footing on the pedestal to thereby stabilize the pedestal andthe base station when the base station is in the elevated position.

In certain embodiments, supporting the base station on the pedestal mayinclude releasably connecting the base station to the pedestal toinhibit unintended separation thereof.

In certain embodiments, the method may further include: facilitatingtakeoff of the UAV from the base station; docking the UAV with the basestation after flight; and nesting the base station within the pedestalfollowing docking of the UAV by returning the base station to theinterior space.

In certain embodiments, nesting the base station within the pedestal mayinclude positioning a well defined by the pedestal between antennas onthe base station.

In another aspect of the present disclosure, a base station is disclosedfor an unmanned aerial vehicle (UAV). The base station includes: anenclosure; a slide mechanism that is connected to the enclosure andwhich is repositionable between a retracted position and an extendedposition; and a cradle that is connected to the slide mechanism andwhich defines a chamber that is configured to receive the UAV such thatthe UAV is movable into and out of the enclosure during repositioning ofthe slide mechanism between the retracted position and the extendedposition. The cradle includes: an upper shell that defines an air inletand an air outlet; a lower shell that is connected to the upper shell;and at least one thermal insulator that is positioned between the uppershell and the lower shell. The lower shell defines a first airflowopening that is in communication with the air inlet and a second airflowopening in communication with the air outlet. The at least one thermalinsulator defines an airflow channel that is in communication with thefirst airflow opening and the second airflow opening and which extendsabout the chamber to facilitate air circulation within the cradle.

In certain embodiments, the at least one thermal insulator may includean upper thermal insulator and a lower thermal insulator.

In certain embodiments, the airflow channel may extend between the upperthermal insulator and the lower thermal insulator.

In certain embodiments, the airflow channel may include a discontinuousconfiguration.

In certain embodiments, the airflow channel may include a first channelportion and a second channel portion.

In certain embodiments, the first channel portion may be incommunication with the air inlet and the first airflow opening, and thesecond channel portion may be in communication with the air outlet andthe second airflow opening.

In certain embodiments, the first channel portion and the second channelportion may be separated by a nose section of the cradle such that thenose section inhibits airflow between the first channel portion and thesecond channel portion to thereby direct airflow from the air inlet,across the chamber, and into the air outlet.

In another aspect of the present disclosure, a base station is disclosedfor an unmanned aerial vehicle (UAV). The base station includes: anenclosure; a slide mechanism that is connected to the enclosure andwhich is repositionable between a retracted position and an extendedposition; a charging hub that is connected to the slide mechanism andwhich is configured for electrical connection to a power source of theUAV; and a cradle that is connected to the slide mechanism and whichdefines a chamber that is configured to receive the UAV such that theUAV is movable into and out of the enclosure during repositioning of theslide mechanism between the retracted position and the extendedposition. The cradle includes: a housing and at least one thermalinsulator. The at least one thermal insulator is located within thehousing and defines an airflow channel that extends discontinuouslyabout the chamber.

In certain embodiments, the housing may define a charging window that isconfigured to receive the charging hub such that the charging hub isextendable into the cradle during repositioning of the slide mechanismbetween the retracted position and the extended position.

In certain embodiments, the housing may define an air inlet and an airoutlet that are positioned on opposite sides of the chamber.

In certain embodiments, the airflow channel may include a first channelportion that is in communication with the air inlet and a second channelportion that is in communication with the air outlet.

In certain embodiments, the first channel portion and the second channelportion may be separated by a nose section of the cradle such that thenose section inhibits airflow therebetween to thereby direct airflowfrom the air inlet, across the chamber, and into the air outlet.

In another aspect of the present disclosure, a base station is disclosedfor an unmanned aerial vehicle (UAV). The base station includes: anenclosure that is configured to receive the UAV and a charging hub thatis operatively connected to the enclosure and which is configured tocharge the UAV. The charging hub includes: a base; an alignment bracketthat is movably supported by the base such that the alignment bracket isrepositionable between a normal position and a deflected position; and acharging member that is configured for electrical connection to the UAV.The charging member is connected to the alignment bracket such that thecharging member and the alignment bracket are movable in unison along anaxis of movement during repositioning of the alignment bracket betweenthe normal position and the deflected position.

In certain embodiments, the charging hub may further include a biasingmember that is positioned between the base and the alignment bracket andwhich is configured to bias the alignment bracket towards the normalposition.

In certain embodiments, the alignment bracket may include an alignmentmember that is configured for insertion into a receptacle defined by theUAV to facilitate proper positioning of the charging member andelectrical connection of the charging hub to the UAV.

In certain embodiments, the alignment member may extend axially forwardof the charging member along the axis of movement.

In certain embodiments, the alignment member may be vertically offsetfrom the biasing member.

In another aspect of the present disclosure, a base station is disclosedfor an unmanned aerial vehicle (UAV). The base station includes: anenclosure having a front end that is configured to receive the UAV and arear end; a cradle that is configured for docking with the UAV and whichis movable in relation to the enclosure via a slide mechanism; a firstelectronics module that is removably connected to the rear end of theenclosure and which is configured to facilitate data processing andcontrol of the base station; and an air circulation module that isconnected to the rear end of the enclosure and which is positioned aboutthe first electronics module to facilitate cooling thereof.

In certain embodiments, the base station may further include a secondelectronics module and a third electronics module.

In certain embodiments, the second electronics module may be removablyconnected to a roof section of the enclosure and may be configured tofacilitate opening and closure of the enclosure, and the thirdelectronics module may be removably connected to the slide mechanism andmay be configured to facilitate repositioning of the cradle, whereby thefirst electronics module, the second electronics module, and the thirdelectronics module may be individually removable from the base station.

In certain embodiments, the first electronics module may include a heatsink.

In certain embodiments, the ducting may define a chamber having an innercontour that corresponds to an outer contour of the heat sink.

In another aspect of the present disclosure, a base station is disclosedfor an unmanned aerial vehicle (UAV). The base station includes: ametallic enclosure; a first electronics module; a second electronicsmodule; and a third electronics module, wherein the first electronicsmodule, the second electronics module, and the third electronics moduleare each configured for individual removal from the metallic enclosure.The metallic enclosure is configured to receive the UAV and includes afront end having a front door and a rear end having a rear door. Therear door is located adjacent to the first electronics module andincludes a metallic panel that is positioned in correspondence with thefirst electronics module so as to create a Faraday cage for the firstelectronics module and thereby reduce electromagnetic emissions from thebase station.

In certain embodiments, the rear door may further include a non-metallicframe.

In certain embodiments, the metallic panel may be connected to thenon-metallic frame.

In certain embodiments, the second electronics module may include anaccess panel that is removably connected to a roof section of themetallic enclosure.

In certain embodiments, the access panel may be removably connected toan inner surface of the roof section via a plurality of mechanicalfasteners such that the second electronics module is accessible fromwithin the metallic enclosure.

In certain embodiments, the mechanical fasteners may be configured toallow for toolless connection of the access panel to the roof sectionand toolless disconnection of the access panel from the roof section.

In certain embodiments, the base station may further include a slidemechanism and a cradle that is connected to the slide mechanism.

In certain embodiments, the slide mechanism may be connected to themetallic enclosure.

In certain embodiments, the slide mechanism may be repositionablebetween a retracted position and an extended position.

In certain embodiments, the cradle may be configured for docking withthe UAV such that the UAV is movable into and out of the metallicenclosure during repositioning of the slide mechanism between theretracted position and the extended position.

In certain embodiments, the third electronics module may be removablyconnected to the slide mechanism such that the third electronics moduleis accessible from within the metallic enclosure upon removal of theUAV.

BRIEF DESCRIPTION OF THE DRAWINGS

The present disclosure is best understood from the following detaileddescription when read in conjunction with the accompanying drawings. Itis emphasized that, according to common practice, the various featuresof the drawings are not to-scale. On the contrary, the dimensions of thevarious features are arbitrarily expanded or reduced for clarity.

FIG. 1 is a front, perspective view of a base station (dock) accordingto the principles of the present disclosure.

FIG. 2 is a partial, side view of the base station shown with oneembodiment of a UAV docked within a cradle of the base station, whichincludes a plurality of propulsion mechanisms (e.g., propellerassemblies), each of which includes a hub and a plurality of propellerblades connected thereto.

FIG. 3 is a partial, side view of the base station shown with analternate embodiment of the UAV seen in FIG. 2 .

FIG. 4 is a bottom, perspective view of a power source of the UAV.

FIG. 5 is a partial, side, perspective view of the power source of theUAV.

FIG. 6 is a side, schematic view of the base station.

FIG. 7 is a partial, rear, perspective view of the base station.

FIG. 8 is a partial, side, perspective view of the base stationillustrating a plurality of actuators that are configured to open andclose a (front) door of the base station.

FIGS. 9 and 10 are partial, top, perspective views of the base stationillustrating the plurality of actuators.

FIG. 11 is a partial, front, perspective view of the base stationillustrating a cap that is supported on a slide mechanism, whichfacilitates movement of the cradle between a retracted position and anextended position.

FIG. 12 is a partial, rear, perspective view of the cap shown overlayedby the door of the base station upon closure.

FIG. 13 is a partial, side, perspective view of the base station withthe cradle shown in the extended position.

FIG. 14 is top, perspective view of the slide mechanism according to oneembodiment of the disclosure, in which the slide mechanism is connected(secured) to an enclosure of the base station via a plurality of firstmounts and a plurality of second mounts.

FIG. 15 is a top, perspective view of the slide mechanism, the firstmounts, and the second mounts.

FIG. 16 is a bottom, plan view of the slide mechanism, the first mounts,and the second mounts.

FIG. 17 is a partial, side, perspective view of the slide mechanism, oneof the first mounts, and one of the second mounts during assembly.

FIG. 18 is a partial, side, perspective view of the slide mechanism, thefirst mount, and the second mount seen in FIG. 17 upon assembly.

FIG. 19 is bottom, perspective view of one of the first mounts.

FIG. 20 is transverse (horizontal), cross-sectional view of one of thefirst mounts.

FIG. 21 is an axial (vertical), cross-sectional view of one of the firstmounts.

FIG. 22 is an axial (vertical), cross-sectional view illustratingconnection of the slide mechanism to the enclosure via one of the firstmounts.

FIG. 23 is a side, perspective view of one of the second mounts.

FIG. 24 is an axial (vertical), cross-sectional view illustratingassembly of the enclosure, the slide mechanism, and one of the secondmounts.

FIG. 25 is a partial, top, perspective view of the slide mechanism, oneof the first mounts, and one of the second mounts during assembly andillustrating a lateral (radial, horizontal) gap between the slidemechanism and the second mount.

FIG. 26 is a side, plan view of the slide mechanism, the first mount,and the second mount seen in FIG. 25 upon assembly and illustrating anaxial (vertical) gap between the slide mechanism and the second mount.

FIG. 27 is a partial, top, perspective view of the base stationillustrating one or more connection antennas and one or more fiducialsthat are supported on a roof section thereof.

FIG. 28 is a partial, top, perspective view of the base stationaccording to an embodiment of the disclosure that includes a pluralityof fiducials on the roof section.

FIG. 29 is a partial, front, perspective view of the base stationillustrating a status indicator.

FIG. 30 is a partial, top, perspective view of the base stationaccording to an embodiment of the disclosure that includes anillumination system on the roof section.

FIG. 31A is a partial, front, perspective view of the base stationduring movement of the cradle into the retracted position after dockingof the UAV.

FIG. 31B is a partial, front, perspective view of the base stationduring movement of the cradle into the retracted position after dockingof the UAV illustrating one embodiment of a contact member that isconfigured to facilitate reconfiguration (e.g., folding) of one or moreantennas on the UAV

FIG. 32 is partial, top, plan view of the base station and the UAV shownin a flight configuration.

FIG. 33 is top, plan view of the UAV shown separated from the basestation.

FIGS. 34A-34C are top, plan views of the UAV shown in the storageconfiguration with the propeller assemblies shown in a variety oforientations.

FIG. 34D is a partial, front, perspective view of the base station andthe UAV during retraction of the UAV into the base station according toone embodiment of the disclosure.

FIG. 35 is a partial, top, plan view of the UAV illustrating desiredpositional ranges for the propeller assemblies of the UAV in the storageconfiguration.

FIG. 36 is a partial, end view of the base station shown with the doorshown in an open position according to one embodiment of the disclosure,which includes engagement members (e.g., bumpers) that are supported bythe actuators and configured to for contact with the propellerassemblies to facilitate reconfiguration of the UAV into the storageconfiguration.

FIG. 37 is a partial, side, plan view of the base station and one of theengagement members.

FIG. 38 is an end view of one of the engagement members shown separatedfrom the base station.

FIG. 39 is a partial, side, plan view of the base station illustratingan (angular) range of motion for the door.

FIG. 40 is a partial, side, plan view of the base station illustratingan (angular) range of motion for the actuators and the engagementmembers.

FIG. 41 illustrates a method of reconfiguring (e.g., folding) thepropeller assemblies of the UAV

FIG. 42 is a top, plan view of one of the propeller assembliesillustrating contact with one of the engagement members.

FIG. 43 is a top, plan view of the propeller assembly and the engagementmember seen in FIG. 42 during folding of the propeller assembly.

FIG. 44 is an enlargement of the area of detail identified in FIG. 43 .

FIG. 45 is side, plan view of an alternate embodiment of the basestation, in which the engagement members are supported by the door.

FIG. 46 is an end, plan view of the base station seen in FIG. 45 .

FIGS. 47 and 48 are opposite side, schematic views of a temperaturecontrol system of the base station, which includes a first air circuit;a second air circuit; and a thermoelectric conditioner (TEC).

FIG. 49 is a partial, side, schematic view of the cradle and the secondair circuit.

FIG. 50 is partial, side, schematic view of the temperature controlsystem.

FIG. 51 is a partial, side, schematic view of the temperature controlsystem illustrating a first heat sink and a second heat sink.

FIG. 52 is a partial, side, schematic view of the first heat sink andthe second heat sink, which is shown located within a plenum of thesecond air circuit.

FIG. 53A is a partial, top, schematic view of the base station accordingto an embodiment of the disclosure that includes one or more heatingelements on the roof section.

FIG. 53B is a is a partial, bottom, schematic view of the base stationillustrating the heating element(s) on the roof section seen in FIG.53A.

FIG. 54 is a front, plan view of the base station shown nested within apedestal.

FIG. 55 is a side, perspective view of the base station and the pedestalseen in FIG. 54 with the base station shown in an elevated position.

FIG. 56 is a rear, perspective view of an insulated cradle according toone embodiment of the disclosure;

FIG. 57 is a rear, perspective view of the insulated cradle seen in FIG.56 with parts separated.

FIG. 58 is a side, perspective view illustrating mating of the insulatedcradle and the plenum of the second air circuit.

FIG. 59 is a partial, rear, perspective view of the base stationaccording to one embodiment of the disclosure, which includes aplurality of heating elements secured to an inner surface of theenclosure.

FIG. 60 is a partial, front, perspective view of the base station withthe (front) door shown in the open position.

FIG. 61 is a partial, rear, perspective view of the base stationaccording to one embodiment of the disclosure, which includes a thermalinterface material located between the enclosure and the heatingelements.

FIG. 62 is a front, perspective view of the base station according toone embodiment of the disclosure in which the status indicator(s) areconfigured to heat the door and/or a sealing member that is supported bythe enclosure and which is configured for engagement with the door.

FIG. 63 is a partial, front, perspective view of an alternate embodimentof the base station, which includes thermally conductive members thatare embedded within the door and/or the sealing member.

FIG. 64 is a partial, top, schematic view of the base stationillustrating an internal fan.

FIG. 65 is a partial, rear, perspective view of the base stationillustrating one or more channels that collect and direct water.

FIG. 66 is a top, perspective view of the UAV shown connected to acharging hub of the base station, which includes: a base; an alignmentbracket; one or more biasing members; a charging member; and a cap.

FIG. 67 is a partial, top, plan view of the UAV and the charging hubshown with the cap removed.

FIG. 68 is a top, perspective view of the charging hub shown separatedfrom the UAV.

FIG. 69 is a front, plan view of the charging hub.

FIG. 70 is a rear, plan view of the charging hub

FIG. 71A is a longitudinal, cross-sectional view of the UAV and thecharging hub taken along line 71A-71A in FIG. 66 with the alignmentbracket shown in a normal position.

FIG. 71B is a longitudinal, cross-sectional view of the UAV and thecharging hub with the alignment bracket shown in a deflected position.

FIG. 72 is a partial, longitudinal, cross-sectional view of the charginghub.

FIG. 73 is a partial, longitudinal, cross-sectional view of the charginghub shown with the charging member removed.

FIG. 74 is a top, plan view of the charging hub shown with the capremoved.

FIG. 75 is a top, plan view of the charging hub according to oneembodiment of the disclosure, which includes a pair of biasing members.

FIG. 76 is a rear, plan view of the base station.

FIG. 77 is a front, perspective view of a (first) electronics moduleincluded in the base station.

FIG. 78 is a front, perspective view of the electronics module seen inFIG. 77 with parts separated.

FIG. 79 is a front, perspective view of the electronics module seen inFIG. 77 shown with an air circulation module.

FIG. 80 is a rear, perspective view illustrating connection of theelectronics module seen in FIG. 77 .

FIG. 81 is a rear, plan view of the base station upon connection of theelectronics module seen in FIG. 77 .

FIG. 82 is a front, perspective view of the base station shown with theair circulation module connected.

FIG. 83 is a rear, perspective view of the base station with a rear doorthereof shown in an open position.

FIG. 84 is a front, perspective view of the rear door of the basestation.

FIG. 85 is a partial, top, perspective view of the base stationillustrating a (second) electronics module.

FIG. 86 is a partial, side, perspective view of the base stationillustrating the electronics module seen in FIG. 85 .

FIG. 87 is a front, perspective view of the base station illustratingthe electronics module seen in FIG. 85 .

FIG. 88 is a partial, front, perspective view of the base stationillustrating a (third) electronics module.

DETAILED DESCRIPTION Overview

The present disclosure relates to a base station for use with a UAV thatis configured to not only charge the power source of the UAV, butregulate the temperature of the power source of the UAV. In variousembodiments of the disclosure, depending upon the environmentalconditions, the base station may be configured to cool the power sourceof the UAV (e.g., when the base station and the UAV are used in hotenvironments) or heat the power source of the UAV (e.g., when the basestation and the UAV are used in cold environments).

To facilitate cooling and/or heating of the power source of the UAV, thebase station includes a temperature control system. The temperaturecontrol system includes: a thermoelectric conditioner (TEC); a first aircircuit that is thermally connected to the TEC and which is configuredto regulate (e.g., increase or decrease) temperature of the TEC; and asecond air circuit that is thermally connected to the TEC such that theTEC is located between the first air circuit and the second air circuit.The second air circuit is configured to direct treated air (e.g., airthat has been either cooled or heated) across the power source of theUAV to thereby heat or cool the power source (subject to environmentalconditions).

To increase functionality and improve operation of the base station, thebase station includes a plurality of additional (ancillary) systems thatare configured to address environmental concerns (e.g., humidity,precipitation, etc.), security concerns (e.g., anti-theft systems andmechanisms), etc. For example, the base station may include: a heatingelement that is supported by a roof section to reduce the presence ofsnow and/or ice; one or more fiducials that facilitate visualidentification of the base station by the UAV; an illumination systemthat improves visibility of the one or more fiducials (e.g., duringnighttime operation); and a visualization system (e.g., a digital imagecapturing device) that supports observation and visual analysis of theenvironment in which the base station and the UAV are located.

The base station includes a cradle that is configured to receive the UAVduring docking and which is extendable from and retractable into thebase station via a slide mechanism. In certain embodiments of thedisclosure, the slide mechanism is (indirectly) connected (secured) tothe base station (e.g., to a sheet metal base) via first and secondmounts, which separate the slide mechanism from the base station inorder to reduce vibration (and other such movement) of the slidemechanism during extension and retraction.

In certain embodiments of the disclosure, upon docking of the UAV withthe base station, propeller assemblies on the UAV may be reconfigured(e.g., folded) from an extended configuration into a collapsedconfiguration, which not only allows for a reduction in the overall sizeof the base station, but inhibits (if not entirely prevents) undesirablecontact with the propeller assemblies. To facilitate suchreconfiguration, the base station includes engagement members, which maybe supported by (connected to) the (front) door of the base station,actuators for the door, or any other suitable structure, and areconfigured for contact with the propeller assemblies to facilitatefolding thereof. More specifically, during retraction of the cradle andthe UAV into the base station, the propeller assemblies are folded viabidirectional rotation into contact with the engagement members.

Referring now to the drawings, FIGS. 1 and 2 illustrate an unmannedaerial vehicle (UAV) 10 and a base (docking) station 100 that isconfigured for automated servicing (e.g., docking, storage, charging,operation, etc.) and accommodation of the UAV 10. While a single UAV 10and a single base station 100 are shown and described herein, in certainembodiments of the disclosure, it is envisioned that a plurality of UAVs10 and a plurality of base stations 100 may be utilized depending, forexample, upon the particular intended use of the UAVs 10. The UAV

The UAV 10 includes one or more propulsion mechanisms (systems) 12 and apower source 14 (e.g., a battery 16). To support autonomous landing anddocking of the UAV 10 with the base station 100, it is envisioned thatthe UAV 10 may follow any suitable process or procedure and may includeany suitable electrical and/or logic components, as described in U.S.application Ser. No. 16/991,122 (“the '122 application”), the entirecontents of which are hereby incorporated by reference.

The propulsion mechanism(s) 12 may include any components and/orstructures suitable for the intended purpose of supporting flight of theUAV 10. For example, in the particular embodiment of the UAV 10 seen inFIGS. 2 and 32 , the propulsion mechanism(s) 12 are configured aspropeller assemblies 18 that include: propeller arms 38; (rotatable)hubs 40 that are supported by the propeller arms 38; and a plurality ofpropeller blades 42 that are connected (secured) to the hubs 40, eitherdirectly or indirectly (operatively). More specifically, the hubs 40each include: a motor 44 (or other such drive mechanism); a rotatabledrive shaft 46, which is connected to the motor 44; and a plurality ofsupports 48, which are connected to (and extend between) the drive shaft46 and the propeller blades 42 such that rotation of the drive shaft 46causes corresponding rotation of the propeller blades 42. It should beappreciated, however, that the particular configuration and/orcomponents of the propulsion mechanism(s) 12 may be varied withoutdeparting from the scope of the present disclosure. FIG. 3 , forexample, illustrates an alternate configuration for the UAV 10.

In the particular embodiment of the UAV 10 illustrated, the UAV 10includes four propeller assemblies 18. More specifically, the UAV 10includes: a (first) rear propeller assembly 18 ri; a (second) rearpropeller assembly 18 rii; a (first) front propeller assembly 18 fi; anda (second) front propeller assembly 18 fii. As seen in FIG. 2 , the rearpropeller assemblies 18 ri, 18 rii and the front propeller assemblies 18fi, 18 fii are oriented in (vertically) opposite directions (e.g., therear propeller assemblies 18 ri, 18 rii are oriented (vertically)upwards and the front propeller assemblies 18 fi, 18 fii are oriented(vertically) downwards), whereby the rear propeller assemblies 18 ri, 18rii are positioned in a first vertical location (e.g., height) and thefront propeller assemblies 18 fi, 18 fii are positioned in a second,lower vertical location (e.g., height). It should be appreciated,however, that the particular number of propeller assemblies 18, theconfiguration of the propeller assemblies 18, the location of thepropeller assemblies 18, and/or the orientation of the propellerassemblies 18 may be varied in alternate embodiments without departingfrom the scope of the present disclosure. As such, embodiments of theUAV 10 including both fewer and greater numbers of propeller assemblies18 are also envisioned herein and would not be beyond the scope of thepresent disclosure.

It is envisioned that the propeller assemblies 18 may include either afixed configuration or a variable configuration. For example, it isenvisioned that the propeller assemblies 18 may be reconfigurablebetween an extended (first) configuration and a collapsed (folded,second) configuration to allow for a reduction in the overall size ofthe UAV 10 (e.g., during entry into the base station 100) and, thus, areduction in the overall size of the base station 100, as described infurther detail below. To facilitate reconfiguration of the propellerassemblies 18 between the extended configuration and the collapsedconfiguration, in certain embodiments, it is envisioned that thepropeller blades 42 may be pivotably connected to the supports 48 viapivot members 50 (FIGS. 32, 42-44 ) (e.g., pins, posts, or the like) soas to facilitate folding of the propeller assemblies 18, further detailsof which are provided below.

The power source 14 is located (e.g., attached to or otherwise supportedon) a lower (bottom) surface of the UAV 10 and includes one or moreconducting (electrical) contacts (not shown) that are configured forengagement (contract) with one or more corresponding conducting(electrical) contacts on the base station 100 to enable charging of thepower source 14, as described in further detail below.

Heat Exchange

As seen in FIGS. 4 and 5 , the power source 14 includes one or morepower cells 20; one or more thermal transfer members 22; and a heatexchanger 24, which defines a lower (bottom) surface of the power source14 and acts as a cover for the power cell(s) 20 and the thermal transfermember(s) 22. The thermal transfer member(s) 22 and the heat exchanger24 are configured to facilitate the transfer of thermal energy betweenthe power source 14 and the ambient (air) to decrease or increasetemperature of the power source 14. For example, depending upon theparticular environment in which the UAV 10 and the base station 100 areemployed, the thermal transfer member(s) 22 and the heat exchanger 24may be utilized to dissipate heat generated by the power source 14during use and/or charging of the UAV 10 (e.g., in hot environments) orto transfer heat to the power source 14 (e.g., in cold environments) tothereby improve efficiency, operation, and/or the usable life of the UAV10 and/or the power source 14.

In the particular embodiment illustrated, the power source 14 includes aplurality of individual (e.g., discrete) power cells 20. It should beappreciated, however, that the particular number and/or configuration ofthe power cells 20 may be varied in alternate embodiments withoutdeparting from the scope of the present disclosure. For example,embodiments of the power source 14 including a single power cell 20 arealso envisioned herein.

The thermal transfer member(s) 22 are thermally connected to, and extendbetween, the power cell(s) 20 and the heat exchanger 24. In theparticular embodiment of the disclosure illustrated, the power source 14includes a plurality of individual (e.g., discrete) thermal transfermembers 22, each of which is associated with (e.g., thermally connectedto) a corresponding power cell 20 (e.g., such that the power source 14includes a corresponding (equal) number of power cells 20 and thermaltransfer members 22). It should be appreciated, however, that theparticular number of the thermal transfer members 22 may be varied inalternate embodiments without departing from the scope of the presentdisclosure and that embodiments of the power source 14 including anunequal number of power cells 20 and thermal transfer members 22 arealso envisioned herein. For example, the present disclosure contemplatesembodiments in which the number of power cells 20 may exceed the numberof thermal transfer members 22 are also envisioned herein (e.g.,embodiments in which the power source 14 includes a single thermaltransfer member 22 that extends between the collection of power cells 20and the heat exchanger 24) as well as embodiments in which the number ofthermal transfer members 22 may exceed the number of power cells 20.

The thermal transfer member(s) 22 may include (e.g., may be formedpartially or entirely from) any material or combination of materialsthat is suitable for the intended purpose of transferring heat between,and thermally connecting, the power cell(s) 20 and the heat exchanger24. For example, in one particular embodiment, it is envisioned that thethermal transfer member(s) 22 may include (e.g., may be formed partiallyor entirely from) graphite. It should be appreciated, however, that theuse of other materials would not be beyond the scope of the presentdisclosure. Additionally, although each thermal transfer member 22 isshown as being unitary in construction (i.e., as being formed from asingle piece of material), in alternate embodiments of the disclosure,it is envisioned that each thermal transfer member 22 may include aseries of individual segments that are connected to each other duringmanufacture, assembly of the power source 14, or at any other suitablepoint in time.

The heat exchanger 24 is thermally connected to the thermal transfermember(s) 22 and is configured to communicate and distribute thermalenergy between the power source 14 and the ambient (air), either awayfrom the power source 14 (e.g., when utilized in hot environments) ortowards the power source 14 (e.g., when utilized in cold environments),and may include (e.g., may be formed partially or entirely from) anymaterial or combination of materials suitable for that intended purpose.For example, it is envisioned that the heat exchanger 24 may include(e.g., may be formed partially or entirely from) aluminum, magnesium,copper, etc.

To increase the available surface area and, thus, the distribution ofthermal energy (either towards or away from the power source 14), incertain embodiments, such as that illustrated throughout the figures,the heat exchanger 24 may include one or more diffusers 26, which may beconfigured in any manner suitable for that intended purpose. Forexample, it is envisioned that the diffuser(s) 26 may be configured aspins, protrusions, ribs, or other such surface irregularities and mayextend axially (e.g., along a longitudinal axis Y) and/or laterally(e.g., a long a transverse axis X) along an outer (bottom) surface 28 ofthe heat exchanger 24. In the particular embodiment of the heatexchanger 24 illustrated throughout the figures, for example, thediffusers 26 are configured as fins 30 that define a plurality ofchannels 32 therebetween, which collectively direct air flow along theheat exchanger 24 to further increase the distribution of thermalenergy.

Although shown as including a plurality of diffusers 26 and channels 32in the particular embodiment of the disclosure illustrated, it should beappreciated that the particular number of the diffusers 26 and/orchannels 32 may be varied in alternate embodiments without departingfrom the scope of the present disclosure. For example, embodiments ofthe heat exchanger 24 including a single diffuser 26 are also envisionedherein.

Base Station Construction

With reference now to FIGS. 4-26 as well, the base station 100 includes:an enclosure (body) 102 having a front end 102 a and a rear end 102 b; a(front) door 104 that is movably connected to the enclosure 102 (at thefront end 102 a); and a cradle 106 that is configured to receive(accommodate) the UAV 10.

The enclosure 102 includes an inner housing (shell) 108 and an outerhousing (cover) 110. The respective inner and outer housings 108, 110are configured as separate, discrete structures that may be connectedtogether in any suitable manner, whether fixedly or removably (e.g., toallow for repeated assembly and disassembly of the base station 100during maintenance, repair, etc.). For example, it is envisioned thatthe respective inner and outer housings 108, 110 may be connected via aplurality of mechanical fasteners (e.g., screws, pins, bolts, clips,etc.), which may be hidden (or otherwise obscured) to inhibit theftand/or unauthorized disassembly of the base station 100.

The inner housing 108 defines an internal cavity 112 and a window 113,each of which is configured to receive and accommodate the UAV 10 toallow for entry of the UAV 10 into the base station 100 and exit of theUAV 10 from the base station 100. Additionally, the inner housing 108provides a mounting surface for various components of the base station100 including, for example, electrical components, actuators, and thelike, which are connected (secured, mounted) to the inner housing 108and support operation of the base station 100.

As described in detail below, the outer housing 110 protects the innerhousing 108 and the various components that are connected (secured,mounted) thereto (e.g., from dust, debris, the ingress of moistureand/or water, etc.), supports various external components of the basestation 100, and provides structural support to the base station 100.For example, in the particular embodiment shown, the outer housing 110includes a sheet metal construction. It should be appreciated, however,that embodiments of the base station 110 in which the outer housing 110may include one or more alternative materials are also envisionedherein.

To facilitate access to the various components accommodated within theouter housing 110 (and/or the inner housing 108), in certainembodiments, it is envisioned that the outer housing 110 may include anaccess panel 114 (FIG. 7 ) to support maintenance, repair, etc., whichmay be incorporated in any suitable location. For example, in theparticular embodiment illustrated, the access panel 114 is located atthe rear end 102 b of the enclosure 102 (e.g., the outer housing 110).It should be appreciated, however, that the particular location of theaccess panel 114 may be varied in alternate embodiments withoutdeparting from the scope of the present disclosure (e.g., the accesspanel 114 may be located on a side of the base station 100, rather thanthe rear end 102 b.

In certain embodiments of the disclosure, it is envisioned that theouter housing 110 may include exterior coloration that not only reducessolar loading (heating), but promotes contrast to facilitatevisualization and/or identification of the base station 100 by the UAV10 during docking, as described in further detail below.

The door 104 is movably connected to the outer housing 110 such that thedoor 104 is repositionable between a (fully) closed position (FIG. 1 ),in which the door 104 conceals the internal cavity 112 and the window113, and an open position (FIG. 6 ), in which the internal cavity 112and the window 113 are exposed. More specifically, the door 104 ismovably connected to a forward frame 116 of the outer housing 110.Although illustrated as being pivotably connected to the forward frame116 in the particular embodiment illustrated throughout the figures, itis also envisioned that the door 104 may be slidably repositionablebetween the closed position and the open position in alternateembodiments of the disclosure.

As discussed below, due to the metallic (e.g., sheet metal) constructionof the outer housing 110 and, thus, the forward frame 116, the forwardframe 116 conducts and facilitates the transfer of thermal energy inboth hot and cold environments. More specifically, in hot environments,the forward frame 116 is operable as a heat sink that draws thermalenergy (heat) away from thermally-sensitive components of the basestation 100, and in cold environments, the forward frame 116 is operableas a thermal conduit that directs thermal energy (heat) towards certaincomponents of the base station 100 to facilitate heating thereof.

To facilitate movement of the door 104 between the closed position andthe open position, the base station 100 includes one or more actuators118 (FIGS. 8-10 ) that extend between the door 104 and the enclosure102. Although shown as including respective first and second actuators118 i, 118 ii in the particular embodiment illustrated, which areconnected (secured) to opposing lateral ends of the door 104 such thatthe actuators 118 i, 118 ii are spaced laterally from each other along awidth W of the enclosure 102, it should be appreciated that the presentdisclosure also contemplates embodiments in which a single actuator 118may be utilized to control the position of the door 104 (e.g., to reducethe overall cost and complexity of the base station 100).

Each actuator 118 includes a motor assembly 120 (e.g., a stepper motor)and a linkage assembly 122 that extends between the motor assembly 120and the door 104. More specifically, each motor assembly 120 isconnected (secured) to the inner housing 108 such that the motorassembly(ies) 120 are located between the inner housing 108 and theouter housing 110, which protects the motor assembly(ies) 120 andinhibits the collection of any dust, debris, etc. The linkage assembly122 extends from the motor assembly 120, through the inner housing 108,and pivotably engages the door 104 such that, upon actuation of themotor assembly 120, the linkage assembly 122 applies a force to the door104 to thereby facilitate movement of the door 104 between the closedposition and the open position.

Each linkage assembly 122 includes: a (threaded) drive screw 124; acarrier 126; a first arm 128; and a second arm 130. The drive screw 124is (operatively) connected to the motor assembly 120 such that actuationof the motor assembly 120 causes rotation of the drive screw 124. Thecarrier 126 is threadably engaged to the drive screw 124 such thatrotation of the drive screw 124 causes axial translation of the carrier126. More specifically, rotation of the drive screw in a first direction(e.g., clockwise) causes forward advancement of the carrier 126 (e.g.,movement of the carrier 126 towards the door 104) and rotation of thedrive screw in a second direction (e.g., counterclockwise) causesrearward advancement of the carrier 126 (e.g., movement of the carrier126 away from the door 104). The first arm 128 includes a first end 132that is connected to the carrier 126 (either fixedly or pivotably) and asecond end 134 that is pivotably connected to the second arm 130. Thesecond arm 130 includes a first end 136 that is pivotably connected tothe second end 134 of the first arm 128 and a second end 138 that ispivotably connected to a bracket 140. The bracket 140 is fixedlyconnected to the door 104 which allows for the transmission of forcefrom the carrier 126 to the door 104 via the arms 128, 130.

The cradle 106 defines respective (first and second) front and rear ends106 a, 106 b (FIGS. 2, 10, 13 ) and a chamber 142 (FIG. 10 ) that isconfigured to receive the UAV 10 during docking so as to facilitate(support) charging of the power source 14. More specifically, the basestation 100 includes a charging hub (assembly) 143 (FIGS. 10, 66-75 )that is configured for engagement with, and electrical connection to,the power source 14 upon receipt of the UAV 10 within the chamber 142 tothereby charge the power source 14, as described in further detailbelow. To facilitate proper docking of the UAV 10 and a properelectrical interface between the power source 14 and the charging hub143, the cradle 106 defines sidewalls 146 that taper inwardly towardsthe chamber 142 so as to define an angled guide surface 148 (FIG. 10 ).The angled guide surface 148 is configured for engagement (contact) withthe UAV 10 to direct the UAV 10 into the chamber 142 so as to facilitateseating of the UAV 10 within the cradle 106.

The cradle 106 is movable between a (fully) retracted position (FIGS. 2,10 ), in which the cradle 106 (and the UAV 10) are positioned within theenclosure 102 (e.g., within the internal cavity 112), a plurality ofpartially retracted positions, as described in further detail below, andan extended position (FIG. 13 ), in which the cradle 106 (and the UAV10) are positioned externally of the enclosure 102 to facilitate dockingwith the UAV 10, whereby the UAV 10 is movable into and out of theenclosure 102. To support movement between the extended and retractedpositions (extension and retraction), the cradle 106 is connected to atelescoping slide mechanism 150, which is also movable between extendedand retracted positions corresponding to those of the cradle 106. Theslide mechanism 150 extends through a window 152 (FIG. 1 ) defined by abezel portion 154 of the forward frame 116 and supports a cap (hatch,cover) 156 (FIGS. 1, 8, 11, 12 ) that is configured in correspondencewith the window 152. The cap 156 is movably (e.g., pivotably) connectedto (supported by) the enclosure 102 (e.g., the forward frame 116 of theouter housing 110) such that the cap 156 is movable between a closedposition (FIGS. 6, 11, 12 ) and an open position (FIGS. 1, 8 ) as thecradle 106 (and the slide mechanism 150) move between the retractedposition and the extended position, respectively. More specifically, thecap 156 moves from the closed position into the open position as thecradle 106 (and the slide mechanism 150) move from the retractedposition into the extended position and such that the cap 156 moves fromthe open position into the closed position as the cradle 106 (and theslide mechanism 150) move from the extended position into the retractedposition, whereby the cap 156 engages the bezel portion 154 and isreceived within the window 152.

In certain embodiments of the disclosure, such as that illustratedthroughout the figures, the cap 156 may include an upstanding tab 158(FIG. 11 ) that is configured for receipt within a corresponding recess160 (FIGS. 8, 12 ) defined in an inner surface 162 of the door 104.Receipt of the tab 158 within the recess 160 not only allows for properclosure of the door 104, but allows for overlayment of the cap 156 bythe door 104 upon closure to facilitate sealing of the enclosure 102 andinhibit (if not entirely prevent) the entry of dust, debris, etc.,through the door 104 and/or the bezel portion 154. Additionally, theengagement between the bezel portion 154, the slide mechanism 150, andthe door 104 (e.g., reception of the tab 158 by the recess 160) improvesthe security of the base station 100 by inhibiting access to the cradle106 and, thus, the UAV 10.

The slide mechanism 150 includes a stationary slide member 151 a (FIG.13 ), which is supported by the enclosure 102, and a movable slidemember 151 b, which is slidably supported by the stationary slide member151 a so as to allow for telescopic movement of the slide mechanism 150between an extended and retracted positions (which correspond to theextended and retracted positions of the cradle 106). It is envisionedthat the stationary slide member 151 a may be positioned about themovable slide member 151 b such that that movable slide member 151 b isreceived by the stationary slide member 151 a, as seen in FIG. 13 , orthat the movable stationary slide member 151 b may be positioned aboutthe stationary slide member 151 a such that that stationary slide member151 a is received by the movable slide member 151 b.

In alternate embodiments of the disclosure, it is envisioned that theslide mechanism 150 may be either directly or indirectly (operatively)connected (secured) to the enclosure 102. For example, in certainembodiments, it is envisioned that the slide mechanism 150 (e.g., thestationary slide member 151 a) may be directly and fixedly (e.g.,non-movably) connected (secured) to a plurality of studs 262 (FIGS. 14,17, 21 ) that extend (vertically) upward from a sheet metal base 264 ofthe enclosure 102 (e.g., towards the slide mechanism 150) and which areconfigured for insertion into openings (apertures) 266 (FIGS. 17, 24, 25) in the slide mechanism 150. Alternatively, it is envisioned that theslide mechanism 150 (e.g., the stationary slide member 151 a) may beindirectly (operatively) connected (secured) to the enclosure 102 via aplurality of mounts 268 (FIGS. 14-26 ), that are located between theenclosure 102 (e.g., the sheet metal base 264) and the slide mechanism150. As described in detail below, positioning of the mounts 268 betweenthe enclosure 102 and the slide mechanism 150 physically separates theslide mechanism 150 from the enclosure 102, which reduces the rigidityof the interface therebetween. Physically separating the slide mechanism150 from the enclosure 102 also increases the tolerance for relativemovement (deflection) between the enclosure 102 and the slide mechanism150 during extension and retraction and reduces (resonant) vibration ofthe slide mechanism 150 and, thus, undesirable movement (e.g., shaking,jittering, etc.). In the particular embodiment of the base station 100illustrated in FIGS. 14-26 , the slide mechanism 150 is connected(secured) to the enclosure 102 via a plurality of first mounts 268 i anda plurality of second mounts 268 ii. The mounts 268 i, 268 ii are eachconfigured to receive one of the studs 262 extending from the base 264of the enclosure 102 and include dissimilar (e.g., non-identicalconfigurations), as described in further detail below (e.g., the mounts268 i include a first configuration and the mounts 268 ii include asecond, different configuration). More specifically, the mounts 268 iare each configured to receive first studs 262 i (FIG. 22 ), whichdefine a first length LSi, and the mounts 268 ii are each configured toreceive second studs 262 ii (FIGS. 17, 18, 24 ), which define a secondlength LSii (FIG. 24 ).

The mounts 268 i define opposing (first and second) ends 270, 272 (FIGS.19, 21 ) having (first and second) female and male interfaces 274, 276,respectively, and each include: a (first) bushing (body, body portion)278; a shank 280; and a (first) fastener 282 (FIGS. 18, 22, 25 ). In theparticular embodiment illustrated in FIGS. 14-26 , the base station 100includes six mounts 268 ia-268 if. More specifically, the mounts 268ia-268 id are located in corner sections (regions) 284 i-284 iv of theslide mechanism 150, respectively, one mount 268 ie that is locatedbetween the corner sections 284 i, 284 ii (e.g., such that the cornersections 284 i, 284 ii are spaced equidistant (or approximatelyequidistant) from the mount 268 ie), and one mount 268 if that islocated between the corner sections 284 iii, 284 iv (e.g., such that thecorner sections 284 iii, 284 iv are spaced equidistant (or approximatelyequidistant) from the mount 268 if). It should be appreciated, however,that the particular number of mounts 268 i may be varied in alternateembodiments without departing from the scope of the present disclosure(e.g., depending upon the particular configuration of the base station100, the slide mechanism 150, etc.). As such, embodiments including bothgreater and fewer numbers of mounts 268 i are envisioned herein andwould not be beyond the scope of the present disclosure.

The bushing 278 includes (e.g., is formed partially or entirely from) acompliant material, which (axially) separates the interfaces 274, 276along a longitudinal axis Y1 of the mount 268 i and absorbs forcescreated during extension and retraction of the slide mechanism 150 so asto reduce vibration, shaking, jittering, etc. At the end 270, thebushing 278 defines an aperture 286, which defines the female interface274 and is configured to receive one of the studs 262 i to facilitateconnection of the bushing 278 to the enclosure 102 (e.g., via the studs262 i). More specifically, as seen in FIG. 22 , the aperture 286 extendsinto, but not through, the bushing 278, whereby the stud 262 ii extendspartially into the bushing 278.

In the particular embodiment illustrated, the aperture 286 includesthreading 288, which is configured for engagement with correspondingthreading 290 (FIG. 22 ) on the studs 262 i such that the bushing 278threadably engages (contacts) the sheet metal base 264 of the enclosure102 (via the studs 262 i). It is envisioned, however, that the mounts268 i and the enclosure 102 may be configured for engagement in anysuitable manner. For example, in alternate embodiments of thedisclosure, it is envisioned that the threading 288, 290 may be omittedand that the mounts 268 i and the studs 262 i may be configured forengagement in a press-fit (interference fit) arrangement.

The shank 280 defines the male interface 276 and extends (vertically)upward from the bushing 278 (e.g., away from the sheet metal base 264)such that the shank 280 is insertable into one of the openings 266(FIGS. 17, 24, 25 ) in the slide mechanism 150. The shank 280 isconfigured for (releasable) connection to (engagement with) the fastener282 (FIGS. 18, 22, 25 ) such that the slide mechanism 150 is securedbetween the bushing 278 and the fastener 282. More specifically, in theparticular embodiment illustrated, the shank 280 and the fastener 282include corresponding threading 292, 294. It is envisioned, however,that the shank 280 and the fastener 282 may be configured for engagementin any manner suitable for the intended purpose of fixing the mounts 268i and the slide mechanism 150 in relation to each other (e.g., so as toinhibit (if not entirely prevent) relative movement therebetween). Forexample, in alternate embodiments, it is envisioned that the threading292, 294 may be omitted and that the shank 280 and the fastener 282 maybe configured for engagement in a press-fit (interference fit)arrangement.

In the particular embodiment illustrated in FIGS. 16-22 , the mounts 268i are configured such that the bushing 278 is in direct contact with theenclosure 102 (e.g., the sheet metal base 264) and the slide mechanism150. Alternatively, however, it is envisioned that the mounts 268 i maybe configured such that the bushing 278 is separated from the enclosure102 (e.g., the sheet metal base 264) and/or the slide mechanism 150. Forexample, FIG. 26 illustrates an embodiment in which the mounts 268 iinclude an intermediate member 296 (e.g., a washer 298, an O-ring, etc.)that is located between the bushing 278 and the slide mechanism 150.

Due to the complaint construction of the bushing 278, duringrepositioning of the slide mechanism 150 between the retracted positionand the extended position, the mounts 268 i undergo deformation (e.g.,expansion and contraction) in the lateral (radial) directions identifiedby the arrows 1 (FIGS. 18, 21 ) and/or the axial (vertical) directionsidentified by the arrows 2. The lateral and/or axial deformationtolerated by the mounts 268 i allows for relative movement between theslide mechanism 150 and the enclosure 102 (e.g., the sheet metal base264), which not only eliminates a direct, rigid connection therebetween,but dampens (absorbs) vibration during repositioning of the slidemechanism 150 so as to increase predictability, consistency, and/oruniformity in movement of the slide mechanism 150.

The mounts 268 ii define opposing (first and second) ends 300, 302 andinclude: a (second) bushing (body, body portion) 304 with a base portion306 and a stem 308 extending therefrom; a channel 310; and a (second)fastener 312. In the particular embodiment illustrated in FIGS. 14-26 ,the base station 100 includes four mounts 268 ii. More specifically, thebase station 100 includes four mounts 268 iia-268 iid that are locatedadjacent (or generally adjacent) to the mounts 268 ia-268 id in thecorner sections 284 i-284 iv of the slide mechanism 150, respectively.It should be appreciated, however, that the particular number of mounts268 ii may be varied in alternate embodiments without departing from thescope of the present disclosure (e.g., depending upon the particularconfiguration of the base station 100, the slide mechanism 150, etc.).As such, embodiments including both greater and fewer numbers of mounts268 ii are envisioned herein and would not be beyond the scope of thepresent disclosure.

In the particular embodiment illustrated, the bushing 304 includes(e.g., is formed partially or entirely from) a compliant material tofurther facilitate force absorption by the mounts 268 ii and furtherreduce vibration of the slide mechanism 150 during extension andretraction. Embodiments of the base station 100 in which the bushing 304may include a non-compliant material, however, are also envisionedherein and would not be beyond the scope of present disclosure.

The base portion 306 defines a first transverse cross-sectionaldimension (e.g., a diameter) D1 (FIG. 24 ) and the stem 308 defines asecond transverse cross-sectional dimension (e.g., a diameter) D2 thatis less than the first transverse cross-sectional dimension D1, wherebythe bushing 304 includes (defines) a non-uniform, stepped transversecross-sectional configuration that varies along a longitudinal axis Y2of the mount 268 ii. More specifically, the stem 308 is configured forinsertion into one of the openings 266 (FIGS. 17, 24, 25 ) in the slidemechanism 150, which defines a third transverse cross-sectionaldimension (e.g., a diameter) D3 (FIG. 25 ) that is less than the firsttransverse cross-sectional dimension D1 and greater than the secondtransverse cross-sectional dimension D2, such that the base portion 306is positioned (located) between the enclosure 102 (e.g., the sheet metalbase 264) and the slide mechanism 150. The differential between thetransverse cross-sectional dimensions D2, D3 respectively defined by thestem 308 and the opening 266 results in the formation (definition) of alateral (radial, horizontal) gap G1 (FIG. 25 ) therebetween. Forexample, in the particular embodiment illustrated, the gap G1 lies(substantially) within the range of (approximately) 0.5 mm to(approximately) 1.5 mm (e.g., (approximately) 1 mm). A gap G1 outside ofthis range, however, is also envisioned herein and would not be beyondthe scope of present disclosure.

The channel 310 extends through the bushing 304 is configured to receiveone of the studs 262 ii such that the stud 262 ii extends through themount 268 ii, which facilities (releasable) connection of (engagementbetween) the stud 262 ii and the fastener 312 such that the slidemechanism 150 is secured between the bushing 304 and the fastener 312 soas to inhibit (if not entirely prevent) relative movement between themounts 268 ii and the enclosure 102 (e.g., the studs 262 ii) whileallowing for relative movement between the mounts 268 ii and the slidemechanism 150, as described in further detail below. For example, it isenvisioned that the bushing 304 may be compressible retained between thefastener 312 and the sheet metal base 264 so as to secure the mount 268i in relation to the enclosure 102.

In the particular embodiment illustrated, the fastener 312 includesthreading 314 (FIG. 24 ) that is configured for engagement with thethreading 290 on the stud 262 ii extending through the mount 268 ii (viathe channel 310). It is envisioned, however, that the studs 262 ii andthe fasteners 312 may be configured for engagement in any mannersuitable for the intended purpose(s) discussed above. For example, inalternate embodiments, it is envisioned that the threading 290, 314 maybe omitted and that the stud 262 ii and the fastener 312 may beconfigured for engagement in a press-fit (interference fit) arrangement.

As seen in FIG. 26 , upon connection of the fastener 312 to the stud 262ii, an axial (vertical) gap G2 is defined between the fastener 312 andthe base portion 306, which is equivalent to a (vertical) height HSdefined by the stem 308 of the bushing 304. For example, in theparticular embodiment illustrated, the gap G2 lies (substantially)within the range of (approximately) 1 mm to (approximately) 2 mm (e.g.,(approximately) 1.5 mm). A gap G2 outside of this range, however, isalso envisioned herein and would not be beyond the scope of presentdisclosure.

The gaps G1, G2 allow for reception of the stem 308 by the opening 266in the slide mechanism 150 in a manner that inhibits (if not entirelyprevents) contact between (engagement of) the mounts 268 ii and theslide mechanism 150 when the slide mechanism 150 is in a normal state(condition) (e.g., when the slide mechanism 150 is stationary betweenperiods of extension and retraction). The gaps G1, G2 also allow formovement of the slide mechanism 150 in relation to the enclosure 102 andthe second mounts 268 ii, which is further facilitated by the compliantmaterial comprising the bushings 278 of the first mounts 268 i, in twodegrees-of-freedom DOF1 (FIGS. 18, 25 ), DOF2 (FIGS. 18, 26 ), which areoriented in orthogonal (or generally orthogonal) relation. Morespecifically, the gaps G1 (FIG. 25 ), G2 (FIG. 26 ) respectively allowfor predetermined lateral (radial) and axial (vertical) movement of theslide mechanism 150 (in relation to the enclosure 102 and the secondmounts 268 ii) so as to limit (restrict) deformation of the mounts 268 iand movement of the slide mechanism 150 during extension and retraction,which inhibits (if not entirely prevents) lateral over-travel (e.g., inthe degree-of-freedom DOF1) and axial over-travel (e.g., in thedegree-of-freedom DOF2). Limiting deformation of the mounts 268 i andmovement of the slide mechanism 150 (in relation to the enclosure 102and the second mounts 268 ii) inhibits (if not entirely prevents) damageto (e.g., shearing of) the mounts 268 i and over-travel of the slidemechanism 150 within the enclosure 102, which reduces (if not entirelyeliminates) any likelihood of undesirable contact between the slidemechanism 150 and the various internal components of the base station100. For example, during docking of the UAV 10, the slide mechanism 150may experience (vertical) deflection under the weight of the UAV 10and/or as a result of the force applied to the cradle 106 duringlanding. Any such (vertical) deflection (e.g., movement of the slidemechanism 150 in the degree-of-freedom DOF2), however, is restricted bythe mounts 268 ii via contact between the slide mechanism 150 and thefastener 312, which also restricts axial (vertical) deformation of themounts 268 i, thus inhibiting (if not entirely preventing) damage to themounts 268 i (e.g., overstretching, tearing) that may otherwise occur.

In the particular embodiment of the base station 100 illustrated inFIGS. 14-26 , the mounts 268 i and the mounts 268 ii includenon-identical (dissimilar) configurations, as described above. It shouldbe appreciated, however, that embodiments of the base station 100including a single variety of mount 268 are also envisioned herein andwould not be beyond the scope of the present disclosure. For example,the present disclosure contemplates an embodiment of the base station100 that is devoid of the mounts 268 ii and which exclusively includesthe mounts 268 i.

In certain embodiments of the disclosure, it is envisioned that the door104 and the cradle 106 may be automatically actuated upon the receipt ofan incoming/docking signal from the UAV 10. For example, it isenvisioned that the incoming/docking signal may automatically engage theactuator(s) 118 to thereby open the door 104. Thereafter, when it isdetermined that the door 104 is fully opened, which may be achievedthrough the employ of Hall sensors (or any other such suitable detectionmechanism), the cradle 106 may be extended via (telescopic) movement ofthe slide mechanism 150.

Anti-Theft and Security Measures

To further improve the security of the base station 100, in certainembodiments of the disclosure, it is envisioned that the door 104 mayinclude a locking mechanism. For example, it is envisioned that the door104 may include a magnetic lock to maintain closure of the door 104 inthe absence of power to prevent inadvertent and/or unauthorized openingof the door 104 and, thus, access to the UAV 10.

Additionally, or alternatively, it is envisioned that the actuator(s)118 (FIGS. 8-10 ) may be configured to resist the application of(manual) force to the door 104, and thereby maintain closure of the door104, by inhibit (if not entirely preventing) the transmission of forcefrom the door 104 to the motor assembly(ies) 120. For example, it isenvisioned that the threading defined by the drive screw 124 may includea fine pitch, which would inhibit (if not entirely prevent) thetransmission of force applied to the door 104 to the carrier(s) 126,thereby maintaining closure of the door 104. Additionally, oralternatively, it is envisioned that the actuator(s) 118 may include asolenoid (or other such mechanism) that is configured to engage alocking pin (or other such member).

Pedestal

With reference to FIG. 1 , in certain embodiments, the base station 100may be configured for use with a pedestal 164 (or other suchfree-standing platform) that is configured to support the base station100 and the UAV 10 in an elevated position (e.g., above the ground).Together, the base station 100 and the pedestal 164 describe a dockingsystem 165 for the UAV 10 that creates free air space to not only reduceturbulence (e.g., propeller wash) during takeoff and landing of the UAV10, but mitigate the entry of debris (e.g., dust, particulate, etc.)into the base station 100.

In certain embodiments of the docking system 165, it is envisioned thatthe pedestal 164 and the base station 100 may include correspondingengagement structures (e.g., pins and holes, detents and recesses, ribsand slots, a footing and a channel, etc.) that are configured forreleasable engagement (connection) to promote proper alignment of thepedestal 164 and the base station 100 and inhibit (if not entirelyprevent) unintended separation of the base station 100 from the pedestal164, such as, for example, in the event that the base station 100 and/orthe pedestal 164 is subjected to an applied force (e.g., a wind gust,impact with an external object, etc.). In one particular embodiment, itis envisioned that the corresponding engagement structures may includeone or more openings and corresponding mechanical fasteners (e.g.,bolts, screws, pins, etc.) that are configured for insertion into theopening(s) to allow for fixed, releasably connection of the pedestal 164and the base station 100.

To inhibit (if not entirely prevent) unauthorized separation of the basestation 100 from the pedestal 164 (e.g., to guard against theft of thebase station 100 and/or the pedestal 164), it is envisioned that thepedestal 164 and the base station 100 may include corresponding eyelets(or other such openings) that are configured to receive a lockabletether, chain, cable, bar, etc.

With reference to FIGS. 54 and 55 as well, the pedestal 164 defines aninterior space 334 having an inner contour 336 that is configured incorrespondence with an outer contour 338 of the base station 100 (e.g.such that a vertical transverse cross-sectional configuration of thepedestal 164 approximates a vertical transverse cross-sectionalconfiguration of the base station 100). The corresponding contours 336,338 respectively defined by the interior space 334 and the base station100 allows for positioning of the base station 100 within the pedestal164 during nonuse (e.g., such that the base station 100 can be sortedwithin the interior space 334 to protect the base station 100 duringtransport, in inclement weather, etc.) such that the docking system 165is reconfigurable between a nested (inactive) configuration(arrangement), as seen in FIG. 54 , in which the base station 100received by the pedestal 164, and a stacked (active) configuration(arrangement), as seen in FIG. 55 , in which the base station 100 (andthe UAV 10) are supported by the pedestal 164 in the elevated position.As seen in FIG. 54 , the pedestal 164 is configured and dimensioned tocreate clearance with the base station 100 about an entire periphery 340(e.g., an exterior envelope) of the base station 100), which inhibits(if not entirely prevents) contact between the pedestal 164 and the basestation 100.

In the particular embodiment illustrated, the pedestal 164 is unitary(e.g., monolithic) in construction and is formed from a single piece of(rigid or semi-rigid) material, which may be either metallic (e.g.,aluminum, sheet metal, steel, etc.) or non-metallic (e.g., plastic,polymeric carbon fiber, etc.). In alternate embodiments of thedisclosure, however, it is envisioned that the pedestal 164 may includea series of individual components that are connected together in anysuitable manner (e.g., via one or more mechanical fasteners, in aninterference fit, etc.).

The pedestal 164 includes a trapezoidal (or generally trapezoidal)vertical cross-sectional configuration that defines: an upper wall 342having a non-linear configuration; first and second side walls 344, 346,respectively, that extend vertically from the upper wall 342 and whicheach include a linear (or generally linear) configuration; and first andsecond base walls 348, 350 that extend laterally inward from the firstand second side walls 344, 346, respectively, and which each include alinear (or generally linear) configuration.

The upper wall 342 includes: a first segment 352 i that extendslaterally inward from the first side wall 344; a second segment 352 iithat extends laterally inward from the second side wall 346; a thirdsegment 352 iii that extends in parallel (or generally parallel)relation to the segments 352 i, 352 ii; a fourth segment 352 iv thatextends between the segments 352 i, 352 iii; and a fifth segment 352 vthat extends between the segments 352 ii, 352 iii. Whereas the segments352 i, 352 ii are vertically aligned (e.g., such that the segments 352i, 352 ii are positioned in the same (or substantially the same)vertical location), the segments 352 iii is vertically offset from thesegments 352 i, 352 ii (e.g., such that the segment 352 iii ispositioned in a different vertical location than the segments 352 i, 352ii) so as to define a well 354. Inclusion of the well 354 increases thestrength and/or rigidity of the upper wall 342 and creates (vertical)clearance with the base station 100 (e.g., the antenna(s) 166).Additionally, the well 354 is configured to receive a power cable 356(FIG. 7 ) of the base station 100 so as to inhibit (if not entirelyprevent) bending, kinking, and/or damage to the power cable 356.

In the particular embodiment illustrated, the segments 352 iv, 352 vsubtend identical (or generally identical) obtuse angles αi, αii withthe segments 352 i, 352 ii, respectively, whereby the well 354 extendsinto a space (gap) 358 defined between the antennas 166. It should beappreciated, however, that the particular configuration of the upperwall 342 and the arrangement of the segments 352 may be varied inalternate embodiments without departing from the scope of the presentdisclosure. For example, embodiments are envisioned in which the upperwall 342 may be configured such that the angles αi, αii are equal (orapproximately equal) to 90°, as are embodiments in which the angles αi,αii may be unequal as well as embodiments in which the segment 352 iiimay be vertically aligned with the segments 352 i, 352 ii so as toeliminate the well 354 such that the upper wall 342 includes a linear(or generally linear) configuration.

To increase stability of the pedestal 164 (e.g., in windy conditions),the sidewalls 344, 346 are angled in relation to the upper wall 342 andthe base walls 348, 350, respectively, whereby the base walls 348, 350extend laterally outward of (beyond) the upper wall 342. Morespecifically, the sidewalls 344, 346 are configured so as torespectively define first and second (acute) angles βi, βii with firstand second reference axes Ri, Rii, which are oriented in orthogonal (orgenerally orthogonal) relation to the base walls 348, 350.

To further increase stability (e.g., on uneven terrain), it isenvisioned that the pedestal 164 may include a plurality of adjustablefootings 360. The footings 360 are configured for removable connectionto (engagement with) the base walls 348, 350 and are reconfigurable tolevel the pedestal 164 and, thus, the base station 100 (e.g., byshortening and lengthening the footings 360).

Takeoff, Landing, and Docking

With reference now to FIGS. 27-31B as well, the base station 100includes a plurality of systems, components, and features that supporttakeoff of the UAV 10, landing of the UAV 10, and docking of the UAV 10with the base station 100 after flight. For example, as described below,the base station 100 may include: one or more connection antennas 166;one or more fiducials 168 that are supported by the enclosure 102; anillumination system 170 that is supported by the enclosure 102; one ormore status indicators 172 that are supported by the enclosure 102; anda visualization system 174 that is supported by the enclosure 102.

Connection Antennas

The base station 100 includes primary connection antenna(s) 166 thatfacilitate wireless communication between the base station 100 and theUAV 10, either directly or indirectly. For example, it is envisionedthat that the primary connection antenna(s) 166 may be utilized tofacilitate communication between the base station 100 and an interveningcommunication point, such as a hangar, a warehouse, etc. In suchembodiments, the primary connection antenna(s) 166 on the base station100 support direct communication with the hangar (or the like), whichwould communicate directly with the UAV 10.

In the particular embodiment seen in FIG. 27 , for example, the basestation 100 includes a pair of primary connection antennas 166 that areconnected (secured) to (or otherwise engaged with) a roof section 176 ofthe outer housing 110. It should be appreciated, however, that theparticular number of primary connection antennas 166 and/or the locationof the primary connection antennas 166 may be varied in alternateembodiments without departing from the scope of the present disclosure.For example, embodiments including a single primary connection antenna166 are also envisioned herein, as are embodiments in which the basestation 100 may include one or more primary connection antennas 166 thatare located on sidewalls of the outer housing 110.

In certain embodiments of the disclosure, it is envisioned that the basestation 100 may include one more secondary communication antennas thatfacilitate communication over cellular and/or WiFi networks and/orsupport GPS functionality. In such embodiments, it is envisioned thatthe primary connection antenna(s) 166 and the secondary communicationantenna(s) may operate in tandem. For example, embodiments areenvisioned in which the primary communication antenna(s) 166 mayfacilitate docking of the UAV 10 with the base station 100 (andcommunication therebetween) while the secondary communication antenna(s)may facilitate communication between the base station 100 and the hangar(or vice versa). Fiducials

The fiducials 168 facilitate not only visual identification of the basestation 100 by the UAV 10, but guidance of the UAV 10 during landing anddocking with the base station 100. To promote or otherwise enhancevisualization and/or recognition of the fiducials 168, it is envisionedthat the outer housing 110 may include contrasting coloration.

In the particular embodiment of the disclosure seen in FIGS. 13, 27, and28 , for example, the base station 100 includes (first and second)fiducials 168 i, 168 ii that are located on (supported by) the roofsection 176 of the outer housing 110 (e.g., between the primaryconnection antennas 166) and a (third) fiducial 168 iii that isassociated with (e.g., located on or adjacent to) the cradle 106. Itshould be appreciated, however, that the particular number of fiducials168 and/or the location(s) thereof, may be varied in alternateembodiments without departing from the scope of the present disclosure.

The fiducial 168 i is initially recognized by the UAV 10 to guide theUAV 10 during approach. The fiducial 168 i defines a (first) surfacearea, which is sufficiently large to allow for visual recognition by theUAV 10 from a desired distance. For example, in certain embodiments, itis envisioned that the (first) surface area defined by the fiducial 168i may lie substantially within the range of (approximately) 40 percentto (approximately) 80 percent of the surface area defined by the roofsection 176. Surface areas for the fiducial 168 i that lie outside thedisclosed range, however, would not be beyond the scope of the presentdisclosure (e.g., to account for advancements in visualizationtechnology utilized in the UAV 10).

The fiducial 168 ii is configured as an identification member 178 thatis recognized by the UAV 10 during approach to the base station 100(e.g., after recognition of the fiducial 168 i), which allows the UAV 10to distinguish amongst a plurality of base stations 100 to facilitateproper pairing (e.g., docking of the UAV 10 to a specific base station100). In certain embodiments of the disclosure, it is envisioned thatthe fiducial 168 i may be fixedly connected to the base station 100(e.g., the roof section 176) and that the fiducial 168 ii may beconfigured for removable connection to the base station 100 (e.g., theroof section 176). Removable connection of the fiducial 168 ii allowsfor the uniform manufacture of a fleet of base stations 100 and thesubsequent attachment of the fiducials 168 ii thereto. Embodiments inwhich the fiducial 168 ii may be integrally (e.g., monolithically)formed with the base station 100, however, would not be beyond thepresent disclosure.

In the particular embodiment illustrated, the fiducial 168 ii defines a(second) surface area, which is less than the (first) surface areadefined by the fiducial 168 i. For example, it is envisioned that the(second) surface area defined by the fiducial 168 ii may liesubstantially within the range of (approximately) 10 percent to(approximately) 50 percent of the (first) surface area defined by thefiducial 168 i. Surface areas for the fiducial 168 ii that lie outsidethe disclosed range, however, would not be beyond the scope of thepresent disclosure (e.g., to account for advancements in visualizationtechnology utilized in the UAV 10).

The fiducial 168 iii is configured as an April tag 180 and is recognizedby the UAV 10 after recognition of the fiducial 168 ii. In theparticular embodiment of the disclosure illustrated, the fiducial 168iii is located on the slide mechanism 150, which inhibits (if notentirely prevents) any interference with air flow across the cradle 106during cooling and/or heating of the power source 14 of the UAV 10,which is discussed in further detail below. Embodiments in which thefiducial 168 iii may be located on the cradle 106 itself, however, arealso envisioned herein and would not be beyond the scope of the presentdisclosure.

Illumination System

The illumination system 170 is configured to improve visibility of thefiducials 168 during nighttime operation. In the particular embodimentof the disclosure illustrated, the illumination system 170 includes oneor more light sources 182 (FIG. 28 ) (e.g., LEDs 184) that are secured(connected, mounted) to, or otherwise supported by, the roof section 176of the outer housing 110 to support lighting (illumination) of thefiducials 168 i, 168 ii. It is envisioned that the illumination system170 may be connected to any suitable power source, whether internal tothe base station 100 (e.g., to the power supply controlled by the mainboard/processor) or external (e.g., to a separate power supply, battery,or the like).

In certain embodiments of the disclosure, it is envisioned that theillumination system 170 may be controlled by the main board/processorand configured to flash or strobe the light source(s) 182 according to aparticular pattern, which can be recognized by the UAV 10 duringapproach to thereby identify the base station 100. In such embodiments,it is envisioned that the illumination system 170 may either supplementor replace the fiducial 168 ii as a means of identifying the basestation 100.

Status Indicators

The status indicator(s) 172 (FIG. 29 ) identify the status of the basestation 100 (e.g., that the base station 100 is ready, requires service,is undergoing the docking procedure with the UAV 10, etc.). Each statusindicator 172 includes an (exterior) light source 173 (e.g., one or moreLEDs 186) that is supported by an outer (exterior, external) surface 116a of the forward frame 116, which not only supports status indication,but illumination of the fiducial 168 iii (FIG. 13 ) and/or the cradle106 (e.g., to facilitate docking of the UAV 10). For example, in oneparticular embodiment, it is envisioned that one or more of the LEDs 186may be configured to emit a colored light (e.g., red, blue, yellow,etc.) and that one or more of the LEDs 186 may be configured to emit awhile light to illuminate the fiducial 168 iii and/or the cradle 106.

In the particular embodiment of the disclosure illustrated in FIG. 29 ,the status indicator(s) 172 are secured (connected, mounted) to, orotherwise supported by, the forward frame 116 of the outer housing 110.It should be appreciated, however, that the particular location of thestatus indicator(s) 172 may be varied in alternate embodiments withoutdeparting from the scope of the present disclosure. It is envisionedthat the status indicator(s) 172 may be connected to any suitable powersource, whether internal to the base station 100 (e.g., to the powersupply controlled by the main board/processor) or external (e.g., to aseparate power supply, battery, or the like).

UAV Storage

In certain embodiments of the disclosure, it is envisioned that the UAV10 may be reconfigurable between a flight (unfolded) configuration (FIG.32 ), in which the propeller assemblies 18 are in the extendedconfiguration, and a storage (folded) configuration (FIGS. 33 and34A-34C), in which each of the propeller assemblies 18 is in thecollapsed configuration and oriented within the positional rangeidentified by the reference character R in FIG. 35 . Reconfiguration ofthe UAV 10 into the storage configuration not only allows for areduction in the overall size of the base station 100, but inhibits (ifnot entirely prevents) undesirable contact between the propellerassemblies 18 and the enclosure 102 (FIG. 32 ) that may otherwise resultin unseating of the UAV 10 from the cradle 106, interference withoperation of the door 104, damage to the various internal components ofthe base station 100, etc.

To support movement from the flight configuration into the storageconfiguration, it is envisioned that the base station 100 may beconfigured for engagement with the propeller assemblies 18 (e.g., duringretraction of the cradle 106). For example, it is envisioned that thebase station 100 may include one or more engagement members that areconfigured to physically interface with (contact) the propellerassemblies 18 to fold the propeller assemblies 18 and move the propellerassemblies 18 into the collapsed configuration during retraction of thecradle 106 and movement of the UAV 10 into the enclosure 102, asdescribed in further detail below. It is envisioned that the engagementmember(s) may be integrated into (or defined by) one or more surface(s)of the enclosure 102 (e.g., the forward frame 116 of the outer housing110). For example, the engagement member(s) may be configured asrollers, brushes, (spring-biased) stoppers, or the like.

In certain embodiments of the disclosure, it is envisioned that theengagement member(s) may be configured for passive interaction with thepropeller assemblies 18, whereby the propeller assemblies 18 are broughtinto contact with the engagement member(s) by virtue of the retractionof the cradle 106. Alternatively, it is envisioned that the engagementmember(s) may be configured for active engagement (interaction) with thepropeller assemblies 18. For example, it is envisioned that theengagement member(s) may be repositionable (reconfigurable) between afirst position (configuration), in which the engagement member(s) arepositioned (configured) to avoid contact with the propeller assemblies18 (e.g., such that the engagement member(s) are located outside thepath followed by the propeller assemblies 18 during retraction of thecradle 106), and a second position (configuration), in which theengagement member(s) are positioned (configured) for contact with thepropeller assemblies 18 (e.g., such that the engagement member(s) arelocated within the path followed by the propeller assemblies 18 duringretraction of the cradle 106).

To allow for additional reductions in the overall size of the basestation 100, it is envisioned that the base station 100 may include oneor more contact members 188 that are configured for engagement (contact)with one or more antennas 34 on the UAV 10 to facilitate reconfiguration(repositioning, folding) thereof between an active (use, unfolded,deployed) configuration (FIG. 2 ), in which the antenna(s) 34 extendoutwardly (away) from a body 36 of the UAV 10, which supports (isconnected to) the power source 14, and a passive (storage, folded,undeployed) configuration, in which the antenna(s) 34 are positionedadjacent to (e.g., in contact (engagement) with the body 36 of the UAV10). Reconfiguration of the antenna(s) 34 from the active configurationinto the passive configuration creates clearance with the variousinternal components of the base station 100 to inhibit (if not entirelyprevent) unintended contact between the UAV 10 and the base station 100during movement of the cradle 106 (and the UAV 10) between the extendedposition (FIG. 13 ) and the retracted position (FIGS. 2, 10 ). In theparticular embodiment of the UAV 10 illustrated throughout the figures,the antenna(s) 34 are biased towards the active configuration via one ormore biasing members (e.g., springs or the like) such that theantenna(s) 34 are automatically reconfigured from the passiveconfiguration into the active configuration as the UAV 10 exits the basestation 100 (e.g., via movement of the cradle 106 from the retractedposition (FIGS. 2, 10 ) into the extended position (FIG. 13 )).

In the embodiment illustrated in FIG. 31A, the contact member 188defines a groove (channel) 189 that is configured to receive theantenna(s) 34 during retraction of the cradle 106 as the UAV 10 iswithdrawn into the enclosure 102. FIG. 31B illustrates anotherembodiment of the contact member 188 that includes a leading (forward)edge 190 and a trailing (rear) edge 192 and defines a (vertical) heightH that varies between the edges 190, 192 so as to defined an angled(chamfered, beveled, ramped) surface 194 that is configured forengagement (contact) with the antenna(s) 34 on the UAV 10. In theparticular embodiment of the disclosure seen in FIG. 31B, each contactmember 188 tapers such that the height H decreases from the leading edge190 towards the trailing edge 192. Embodiments in which each contactmember 188 may taper such that the height H increases from the leadingedge 190 towards the trailing edge 192 are also envisioned herein andwould not be beyond the scope of the present disclosure (e.g., dependingupon the particular configuration and/or location of the antenna(s) 34on the UAV 10, spatial constraints of the enclosure 102, etc.).

In the embodiments illustrated in FIGS. 31A and 31B, the base station100 includes a single contact member 188 that is secured (connected) to(or otherwise engaged with) an inner (e.g., upper) surface 196 of theinner housing 108. It should be appreciated, however, that theparticular number of contact members 188 and/or the location of thecontact member(s) 188 may be varied in alternate embodiments withoutdeparting from the scope of the present disclosure (e.g., depending uponthe number of antennas 34 on the UAV 10 and/or the location thereof).For example, embodiments including multiple contact members 188 are alsoenvisioned herein, as are embodiments in which the base station 100 mayinclude one or more contact members 188 that are located on sidewalls198 of the inner housing 108.

It is envisioned that the contact member(s) 188 may be secured(connected) to the inner housing 108 in any suitable manner. Forexample, it is envisioned that the contact member(s) 188 may beintegrally (e.g., monolithically) formed with the inner housing 108 orthat the contact member(s) 188 and the inner housing 108 may be formedas separate, discrete structures, which may be secured (connected)together via one or more mechanical fasteners, an adhesive, etc.

Folding of the Propeller Assemblies

In certain embodiments of the disclosure, as indicated above, it isenvisioned that the base station 100 may include one or more engagementmembers, which are identified by the reference character 316 (FIGS. 34D,36-40 ), that are configured to facilitate movement of the propellerassemblies 18 into the collapsed configuration during retraction of thecradle 106 and the UAV 10 into the enclosure 102. The engagement members316 each include a mounting bracket 318 and a bumper 320 that issupported by (secured, connected to) the mounting bracket 318 such thatthe bumpers 320 contact (engage) the propeller assemblies 18 duringretraction of the UAV into the enclosure 102, which results in repeated,consistent positioning of the propeller assemblies 18 within thepositional ranges R (FIG. 35 ), as described in further detail below.

In the particular embodiment of the disclosure illustrated, the basestation 100 includes first and second engagement members 316 i, 316 iithat are (non-movably) supported by the actuators 118 i, 118 ii,respectively, such that the engagement members 316 i, 316 ii are spacedlaterally from each other along the width W of the enclosure 102. Morespecifically, the engagement members 316 i, 316 ii are fixedly connectedto outer (lateral) faces 322 of the linkage assemblies 122 and arepositioned outside (laterally outward of) the hubs 40 of the propellerassemblies 18 (e.g., in line with the propeller arms 38), which allowsthe UAV 10 to pass between the engagement members 316 i, 316 ii duringretraction of the cradle 106 into the enclosure 102. It should beappreciated, however, that the particular location of the engagementmembers 316 may be altered in various embodiments without departing fromthe scope of the present disclosure (e.g., depending upon the particularconfiguration of the UAV 10, the desired positions of the propellerassemblies 18 in the collapsed configuration, etc.). For example, thepresent disclosure envisions an embodiment in which the engagementmembers 316 may be (non-movably) supported by (e.g., secured, connectedto) the door 104, as described in further detail below.

The mounting brackets 318 may be connected to the actuators 118 (e.g.,the linkage assemblies 122) in any suitable manner. For example, in theparticular embodiment seen in FIGS. 36-38 , the mounting brackets 318are configured for (releasable) connection to the actuators 118 via oneor more mechanical fasteners 324 (e.g., screws, pins, bolts, clips,etc.), which simplifies assembly and disassembly and facilitates repair,replacement, etc. Alternatively, however, it is envisioned that that themounting brackets 318 and the actuators 118 may be configured forconnection in a press-fit (interference fit) arrangement, or that themounting brackets 318 and the actuators 118 may be fixedly(non-removably) connected. For example, in certain embodiments, it isenvisioned that the mounting brackets 318 and the actuators 118 may beintegrally (e.g., monolithically) formed.

Mounting of the engagement members 316 to the actuators 118 allows thevertical positions thereof to be adjusted with opening and closure ofthe door 104 so as to facilitate proper contact with the propellerassemblies 18, as described in further detail below, while inhibiting(if not entirely preventing) interference with operation of the door 104and unintended contact between the engagement members 316 and thevarious internal components of the base station 100. Additionally, withreference to FIGS. 39 and 40 , mounting the engagement members 316 tothe actuators 118 allows for a reduction in the angular range of motion(path) A1 followed by the actuators 118 and, thus, the engagementmembers 316, during opening and closure of the door 104 when compared tothe angular range of motion (path) A2 followed by the door 104 itself.The reduced angular path A1 allows the vertical positions of theengagement members 316 to be adjusted with less angular variation andallows for a reduction in a height (length) HE (FIG. 38 ) of theengagement members 316, which further reduces any likelihood ofunintended contact between the engagement members 316 and the variousinternal components of the base station 100, the enclosure 102 (e.g.,the forward frame 116 (FIG. 36 )), etc.

In the particular embodiment of the disclosure seen in FIGS. 36-38 , thebumpers 320 include (e.g., are formed partially or entirely from) one ormore compliant (flexible) materials, the stiffness of which may bealtered by varying one or more parameters of the bumpers 320. Forexample, the stiffness of the bumpers 320 may be altered by varying theheight HE (FIG. 38 ), a (lateral) thickness T of the bumpers 320, theconfiguration (e.g., the shape, profile) of the bumpers 320, thedurometer of the material(s) selected, etc. The use of compliantmaterial(s) facilitates folding of the propeller assemblies 18 whileallowing for resilient deflection (e.g., bending) of the bumpers 320,which inhibits (if not entirely prevents) spearing of the bumpers 320 bythe propeller blades 42 and unseating of the UAV 10 from the cradle 106that might otherwise occur. The use of compliant material(s) also allowsthe bumpers 320 to return to their normal (undeflected) positions uponsufficient retraction of the UAV 10 to facilitate subsequent contactwith the propeller assemblies 18.

While the bumpers 320 are illustrated as including a rubberized,weather-resistant, and abrasion-resistant material in the particularembodiment of the disclosure seen in FIGS. 36-38 , it is envisioned thatthe bumpers 320 may include any material(s) that support the operationand functionality described herein.

The bumpers 320 include a first (upper) end portion 326 that extendsfrom (is connected to) the corresponding mounting bracket 318 and asecond (lower) end portion 328. In the particular embodiment seen inFIGS. 36-38 , the second end portion 328 defines an angled (chamfered,beveled, ramped) surface 330. It is envisioned that the angled surface330 may guide the bumpers 320 over the propeller assemblies 18 duringretraction of the UAV 10 (e.g., to reduce the force applied to the UAV10 by the engagement members 316). Embodiments devoid of the angledsurface 330, however, are also envisioned herein and would not be beyondthe scope of the present disclosure

With reference now to FIGS. 2, 32, and 35-41 , upon docking of the UAV10 with the base station 100, the door 104 is moved from the closedposition (FIG. 1 ) into the open position (FIGS. 1, 36 ), and the cradle106 begins to retract into the UAV 10 (e.g., during a first stage ofretraction), which brings the rear propeller assemblies 18 ri, 18 riiinto alignment (or general alignment) with the engagement members 316.With the cradle 106 in a first partially retracted position, the door104 is lowered (e.g., moved into a first partially closed position) andthe rear propeller assemblies 18 ri, 18 rii are actively rotated (e.g.,via actuation of the corresponding motors 44 (FIG. 2 )). Lowering of thedoor 104 facilitates contact (engagement) with the antenna(s) 34 (FIG. 2) and reconfiguration thereof between the active configuration and thepassive configuration as well as adjustment in the vertical positions ofthe engagement members 316 (FIGS. 39, 40 ), and active rotation of therear propeller assemblies 18 ri, 18 rii causes the propeller blades 42to contact (engage) the engagement members 316 (throughout the followingdiscussion, rotation of the propeller assemblies 18 is described from apoint-of-view located vertically above the UAV 10). More specifically,the rear propeller assembly 18 ri is rotated in a first direction (e.g.,clockwise) and the rear propeller assembly 18 rii is rotated in asecond, opposite direction (e.g., counterclockwise). Upon contact withthe engagement members 316, continued rotation of the rear propellerassemblies 18 ri, 18 rii causes the propeller blades 42 to pivot aboutthe pivot members 50 (FIG. 32 ), which results in partial folding of therear propeller assemblies 18 ri, 18 rii and movement of the rearpropeller assemblies 18 ri, 18 rii from the extended configurationtowards the collapsed configuration.

Following partial folding of the rear propeller assemblies 18 ri, 18rii, retraction of the cradle 106 continues (e.g., during a second stageof retraction), which moves the cradle 106 into a second partiallyretracted position and reconfigures (folds) the antenna(s) 34 from theactive configuration into the passive configuration (e.g., via contact(engagement) with the door 104). The rear propeller assemblies 18 ri, 18rii are then actively rotated (e.g., via actuation of the correspondingmotors 44) such that the propeller blades 42 are again brought intocontact (engagement) with the engagement members 316. More specifically,the rear propeller assembly 18 ri is rotated in the second direction(e.g., counterclockwise) and the rear propeller assembly 18 rii isrotated in the first direction (e.g., clockwise), which completesfolding of the rear propeller assemblies 18 ri, 18 rii such that rearpropeller assemblies 18 ri, 18 rii are oriented within the desiredpositional ranges R (FIG. 35 ). Folding of the rear propeller assemblies18 ri, 18 rii is thus performed in two stages (e.g., a first stage, inwhich the rear propeller assemblies 18 ri, 18 rii are partially folded,and a second stage, in which the rear propeller assemblies 18 ri, 18 riiare completely folded).

In certain embodiments of the disclosure, it is envisioned that the rearpropeller assemblies 18 ri, 18 rii may be oriented forwardly (e.g.,towards the front propeller assemblies 18 fi, 18 fii and the door 104)upon complete folding, as seen in FIG. 34C (for example).

Following complete folding of the rear propeller assemblies 18 ri, 18rii, retraction of the cradle 106 continues (e.g., during a third stageof retraction) as the cradle 106 moves into a third partially retractedposition, and the door 104 is lowered (e.g., into a second partiallyclosed position). Retraction of the cradle 106 brings the frontpropeller assemblies 18 fi, 18 fii into alignment (or general alignment)with the engagement members 316, and lowering of the door 104 adjuststhe vertical positions of the engagement members 316 (FIGS. 39, 40 ) tofacilitate contact (engagement) with the front propeller assemblies 18fi, 18 fii, which accommodates (compensates for) the difference in thevertical locations (heights) between the rear propeller assemblies 18ri, 18 rii and the front propeller assemblies 18 fi, 18 fii.

The front propeller assemblies 18 fi, 18 fii are then actively rotated(e.g., via actuation of the corresponding motors 44) such that thepropeller blades 42 are brought into contact (engagement) with theengagement members 316. More specifically, the front propeller assembly18 fi is rotated in the second direction and the front propellerassembly 18 fii is rotated in the first direction. Upon contact with theengagement members 316, continued rotation of the front propellerassemblies 18 fi, 18 fii causes the propeller blades 42 to pivot aboutthe pivot members 50 (FIG. 32 ), which results in partial folding of thefront propeller assemblies 18 fi, 18 fii and movement of the frontpropeller assemblies 18 fi, 18 fii from the extended configurationtowards the collapsed configuration.

Thereafter, retraction of the cradle 106 continues (e.g., during afourth stage of retraction) until the cradle 106 is moved into the fullyretracted position. As the cradle 106 is moved into the fully retractedposition, the cap 156 (FIGS. 1, 8, 11, 12 ) moves into the closedposition so as to engage the bezel portion 154, and the front propellerassemblies 18 fi, 18 fii are subjected to additional, passive rotation,during which, the corresponding motors 44 are inactive. Morespecifically, retraction of the cradle 106 causes the front propellerassembly 18 fi to rotate in the first direction via contact with theengagement members 316 i and the front propeller assembly 18 fii torotate in the second direction via contact with the engagement member316 ii, which results in forward orientation of the front propellerassemblies 18 fi, 18 fii (e.g., such that the front propeller assemblies18 fi, 18 fii are oriented away from the rear propeller assemblies 18ri, 18 rii and towards the door 104), as seen in FIG. 34D.

The door 104 is then lowered further (e.g., into a third partiallyclosed position) and the orientation of the front propeller assemblies18 fi, 18 fii is altered so as to inhibit (if not entirely prevent)contact between the front propeller assemblies 18 fi, 18 fii and thedoor 104 during (final) closure. More specifically, the orientation ofthe front propeller assemblies 18 fi, 18 fii is reversed such that thefront propeller assemblies 18 fi, 18 fii are oriented rearwardly (e.g.,towards the rear propeller assemblies 18 ri, 18 rii and away from thedoor 104), as seen in FIG. 34C (for example), which completes folding ofthe front propeller assemblies 18 fi, 18 fii such that the frontpropeller assemblies 18 fi, 18 fii are oriented within the desiredpositional ranges R (FIG. 35 ). To reverse the orientation of the frontpropeller assemblies 18 fi, 18 fii, in the particular embodimentillustrated, the front propeller assemblies 18 fi, 18 fii are activelyrotated (e.g., via actuation of the corresponding motors 44) in thefirst and second directions, respectively. Folding of the frontpropeller assemblies 18 fi, 18 fii is, thus, performed in three stages(e.g., a first stage, in which the front propeller assemblies 18 fi, 18fii are partially folded via active rotation, a second stage, in whichthe front propeller assemblies 18 fi, 18 fii are partially folded viapassive rotation, and a third stage, in which the orientations of thefront propeller assemblies 18 fi, 18 fii are reversed).

Following complete retraction of the cradle 106 and the UAV 10 into theenclosure 102, the door 104 is lowered into the (fully) closed position.

In certain embodiments of the disclosure, it is envisioned that thepropeller assemblies 18 may undergo a final stage rotation (e.g., athird stage of rotation for the rear propeller assemblies 18 ri, 18 riiand a fourth stage of rotation for the front propeller assemblies 18 fi,18 fii). In the final stage of rotation, the orientations of thepropeller assemblies 18 are altered in order to avoid contact with thevarious internal components of the docking station 100 (e.g., duringsubsequent extension of the cradle 106 and the UAV 10). It is envisionedthat particular orientations of the propeller assemblies 18 achievedduring the final stage of rotation may be varied depending upon theparticular locations and/or configurations of the various internalcomponents of the docking station 100. For example, embodiments areenvisioned in which the front propeller assemblies 18 fi, 18 fii and therear propeller assemblies 18 ri, 18 rii may be oriented in the samedirection, as are embodiments in which the front propeller assemblies 18fi, 18 fii and the rear propeller assemblies 18 ri, 18 rii may beoriented in different directions and embodiments in which each of thepropeller assemblies 18 fi, 18 fii, 18 ri, 18 rii may be orienteddifferently. The present disclosure also contemplates embodiments inwhich the final stage rotation may only be performed on certainpropeller assemblies 18. For example, it is envisioned that the finalstage of rotation may only be performed on the front propellerassemblies 18 fi, 18 fii, the rear propeller assemblies 18 ri, 18 rii,the front propeller assembly 18 fi and the rear propeller assembly 18rii, etc.

During the aforedescribed sequence, educated (informed) positioning ofthe door 104 (e.g., the ability of the docking station 100 to controland vary the position (height) of the door 104 and, thus, the engagementmembers 316) reduces any likelihood of unintended contact between theengagement members 316 and the UAV 10. More specifically, allowing theengagement members 316 to remain in an elevated vertical position duringretraction of the cradle 106 reduces any likelihood of spearing of theengagement members 316 by the propeller assemblies 18 and unseating ofthe UAV 10 from the cradle 106 that may otherwise occur. Educatedpositioning of the door 104 also allows for adjustments in theflexibility of the engagement members 316. More specifically, loweringthe vertical positions of the engagement members 316 and reducingspacing with the propeller assemblies 18 effectively increases thestiffness of the engagement members 316, which facilitates and supportsreconfiguration of the propeller assemblies 18 in the manner discussedabove.

Additionally, the bidirectional rotation of the propeller assemblies 18discussed in connection with the aforedescribed sequence (e.g., rotationof the propeller assemblies 18 in the first and second directions) isdictated by the specific configuration of the propeller assemblies 18included in the particular embodiment of the UAV 10 illustrated. Forexample, with reference to FIGS. 42-44 , the propeller assemblies 18included on the UAV 10 define hard stops 52, which are configured forcontact with an adjacent propeller blade 42 to limit continued rotationthereof. The bidirectional rotation of the propeller assemblies 18discussed above accounts for (accommodates) the hard stops 52, however,and allows for reconfiguration of the propeller assemblies 18 in theaforedescribed manner. More specifically, rotation of the propellerassemblies 18 in the first direction (e.g., clockwise), which isidentified by the arrow 3 (FIG. 42 ), causes engagement (contact)between the propeller blades 42 and the corresponding hard stops 52, asseen in FIGS. 43 and 44 , which results in partial folding of thepropeller assemblies 18. Thereafter, the propeller assemblies 18 arerotated in the opposite, second direction (e.g., counterclockwise),which is identified by the arrow 4, to complete folding of the propellerassemblies 18. Embodiments of the UAV 10 are also envisioned, however,in which the propeller assemblies 18 (e.g., the propeller blades 42and/or the hard stops 52) may be reconfigured (altered) so as to allowfor unidirectional rotation during reconfiguration from the extendedconfiguration into the collapsed configuration and would not be beyondthe scope of the present disclosure.

During reconfiguration of the propeller assemblies 18, active rotationof the propeller assemblies 18 can be precisely controlled by varyingthe speed, the duration, and the direction of rotation (e.g., viaembedded programming in the UAV 10 and/or the docking station 100).Additionally, feedback from the motors 44 (FIGS. 2, 42-44 ) can beutilized to detect contact between the propeller blades 42 and the hardstops 52. For example, upon contact between a propeller blade 42 and thecorresponding hard stop 52, a current spike may be detected in the motor44. In such embodiments, upon exceeding a threshold current, the motor44 may be caused to rotate the propeller assembly 18 in the oppositedirection or to halt rotation altogether.

In an alternate embodiment of the disclosure, during a differentsequence, it is envisioned that the motors 44 remain inactive and thatfolding of the propeller assemblies 18 may be accomplished solely viacontact (engagement) with the engagement members 316. In suchembodiments, the engagement members 316 (e.g., the bumper 320) act asguides that inhibit (if not entirely prevent) unintended contact betweenthe propeller assemblies 18 and the enclosure 102 (e.g., spearing of theenclosure 102 by the propeller assemblies 18) during retraction of thecradle 106. More specifically, the engagement members 316 deflect thepropeller blades 42 inwardly so as to inhibit (if not entirely prevent)contact with the forward frame 116 (FIG. 36 ) (e.g., adjacent to thedoor 104), which allows for folding of the propeller assemblies 18during retraction of the cradle 106 via contact with the sidewalls 198(FIGS. 31A, 36 ) of the inner housing 108. In order to facilitatefolding of the propeller assemblies 18, it is envisioned that thevisualization system 174 (FIG. 31B) may be utilized to verify that thepropeller assemblies 18 are positioned properly (e.g., that thepropeller blades 42 have been successfully deflected so as to avoidcontact with the forward frame 116) prior to continued retraction of thecradle 106.

With reference now to FIGS. 45 and 46 , in an alternate embodiment ofthe base station 100, it is envisioned that the engagement members 316may be (non-movably) supported by (e.g., secured, connected to) the door104, as mentioned above. In the particular embodiment illustrated, theengagement members 316 are configured as bumpers 332 that each include acylindrical (or generally cylindrical) configuration. It should beappreciated, however, that the configuration of the bumpers 332 may bevaried without departing from the scope of the present disclosure. Forexample, it is envisioned that the bumpers 332 may be replaced by theaforedescribed bumpers 320.

The bumpers 332 are positioned inside (laterally inward of) the hubs 40(FIGS. 32, 33, 35 ) of the propeller assemblies 18 (e.g., in line withthe propeller arms 38), which allows the propeller assemblies 18 to beoriented in alignment (or general alignment) with the propeller arms 38in the collapsed configuration, as seen in FIG. 34B.

Temperature Control System

With reference now to FIGS. 47-52 , the base station 100 includes atemperature control (e.g., heating and cooling) system 200 that isconnected to the cradle 106 and which is configured to thermallycondition (e.g., cool and heat) the power source 14 (FIGS. 2, 4, 5 ) ofthe UAV 10 when the UAV 10 is docked in the base station 100 (subject toenvironmental conditions). In the particular embodiment of thedisclosure illustrated throughout the figures, the temperature controlsystem 200 is configured to cool the power source 14 of the UAV 10(e.g., when the UAV 10 and the base station 100 are operated in hotenvironments). It should be appreciated, however, that embodiments inwhich the temperature control system 200 may be configured to heat thepower source 14 of the UAV 10 (e.g., when the UAV 10 and the basestation 100 are operated in cold environments) are also envisionedherein and would not be beyond the scope of the present disclosure, asdescribed in further detail below.

The temperature control system 200 includes: an upper air circuit 202; alower air circuit 204; and a thermoelectric conditioner (TEC) 206 thatis thermally connected to, and located between, the respective upper andlower air circuits 202, 204.

The upper air circuit 202 is an open system that receives and circulatesambient air, which may be sourced from within the base station 100 orexternally of the base station 100 (e.g., via an air intake) to vary(regulate) the temperature of the TEC 206. The upper air circuit 202includes: an upper (first) plenum 208; an upper (first) air circulator210; and an upper (first) heat sink 212.

The upper plenum 208 includes an (upper) ducting system 214 thatreceives and circulates the ambient air. The ducting system 214 mayinclude any suitable material (or combination of materials) and mayinclude either a unitary configuration, in which the upper plenum 208 isformed from a single piece of material, or a segmented configuration, inwhich the upper plenum 208 is formed from a plurality of segments thatare connected together (e.g., via one or more mechanical fasteners, anadhesive, in an interference fit, etc.). In certain embodiments, it isenvisioned that the upper plenum 208 may also include one or moresensors that are configured to detect and monitor temperature, humidity,etc. within the upper plenum 208.

The upper air circulator 210 supports and directs air flow through theupper plenum 208 and across the upper heat sink 212 to vary airtemperature within the upper air 202 and thereby regulate thetemperature of the TEC 206, as described in further detail below. Theupper air circulator 210 may include any structure or mechanism suitablefor that intended purpose and may be positioned in any locationsuitable. For example, in the illustrated embodiment, the upper aircirculator 210 is configured as a fan 216 (e.g., an axial fan) that islocated within the upper plenum 208 (e.g., within the ducting system214). It is also envisioned, however, that the upper air circulator 210may be located externally of the upper plenum 208. For example, theupper air circulator 210 may be connected to (or otherwise supported on)an outer surface 218 of the ducting system 214.

The upper heat sink 212 (FIGS. 51, 52 ) is connected to (e.g., locatedwithin) the upper plenum 208 and is configured to alter the temperatureof the air circulated through the upper air circuit 202. For example,when the temperature control system 200 is utilized to cool the powersource 14 (FIGS. 2, 4, 5 ) of the UAV 10, the upper heat sink 212absorbs and distributes thermal energy (heat) generated by the TEC 206to lower the temperature of the air flowing through the upper plenum208, as described in further detail below. To increase the absorptionand distribution of thermal energy by the upper heat sink 212, air flowthrough the upper plenum 208 and, thus, air flow across the upper heatsink 212, may be increased by increasing the speed of the upper aircirculator 210 (e.g., by increasing power to the fan 216).

The lower air circuit 204 includes a lower (second) plenum 220; a lower(second) air circulator 222; and a lower (second) heat sink 224 and isconfigured as a closed system. As such, in contrast to the upper aircircuit 202, rather than drawing in additional ambient air, the lowerair circuit 204 continuously circulates the air that is naturallypresent within the lower plenum 220.

The lower plenum 220 includes a (lower) ducting system 226 that directsair flow across the cradle 106 and the power source 14 of the UAV 10when the UAV 10 is docked within the base station 100 and may includeany suitable material (or combination of materials). The lower plenum220 (e.g., the ducting system 226) includes a segmented (non-unitary)configuration that defines a rear (first, fixed) section 228 and aforward (second, movable) section 230 that is movable in relation to therear section 228. In various embodiments of the disclosure, it isenvisioned that the sections 228, 230 may include either a unitaryconfiguration, in which the sections 228, 230 are each formed from asingle piece of material, or a segmented configuration, in which thesections 228, 230 are formed from a plurality of segments that areconnected together (e.g., via one or more mechanical fasteners, anadhesive, in an interference fit, etc.). In certain embodiments, it isenvisioned that the lower plenum 220 may also include one or moresensors that are configured to detect and monitor temperature, humidity,etc. within the upper plenum 208.

The rear section 228 of the lower plenum 220 is fixedly secured(connected) to the TEC 206 and, as such, is fixed in relation to theupper air circuit 202. The forward section 230 of the lower plenum 220is secured (connected) to the cradle 106 and is movable therewith duringrepositioning of the cradle 106 between the retracted position (FIGS. 2,10 ) and the extended position (FIG. 13 ). As such, throughout thefollowing disclosure, any references to the cradle 106 should beunderstood as referring to the assembly of the cradle 106 and theforward section 230 of the lower plenum 220.

The forward section 230 of the lower plenum 220 receives air from therear section 228 and defines an air inlet 232 and an air outlet 234,which are provided in (defined by) the cradle 106 and are located onopposite sides 142 a, 142 b of the chamber 142). The air inlet 232 andthe air outlet 234 each include one or more vents 235 (e.g., slits,apertures, or other such openings) that extend through the cradle 106(e.g., the sidewalls 146) and into the chamber 142. The vents 235facilitate air flow into and across the chamber 142 by directing airconditioned by the lower air circuit 204 into the cradle 106 and acrossthe power source 14 of the UAV 10 when the UAV 10 is docked in the basestation 100. More specifically, the air inlet 232 is configured todirect air into the cradle 106 and across the power source 14 of the UAV10 and the air outlet 234 is configured to receive the air directedacross the power source 14 and redirect the air through the lower plenum220 and across the lower heat sink 224, as described in further detailbelow.

Although shown as extending entirely about the cradle 106 in theparticular embodiment illustrated throughout the figures, embodimentsare also envisioned in which the forward section 230 of the lower plenum220 may only partially circumscribe the cradle 106. For example,embodiments are envisioned in which the forward section 230 of the lowerplenum 220 may include opposite terminal ends that respectively definethe air inlet 232 and the air outlet 234.

Additionally, while the forward section 230 of the lower plenum 220 andthe cradle 106 are illustrated as being integrally (e.g.,monolithically) formed in the illustrated embodiment, it is alsoenvisioned that the lower plenum 220 and the cradle 106 may beconfigured for releasable (detachable) engagement to allow for repeatedconnection and disconnection of the lower plenum 220 and the cradle 106(e.g., via corresponding engagement structures such as detents, clips,fasteners, or the like).

The lower air circulator 222 supports and directs air flow through thelower plenum 220 and across the lower heat sink 224 to thermallycondition the air within the lower air circuit 204 (e.g., vary thetemperature thereof) and thereby heat or cool the power source 14 of theUAV 10, as described in further detail below. The lower air circulator222 may include any structure or mechanism suitable for that intendedpurpose and may be positioned in any location suitable. For example, inthe illustrated embodiment, the lower air circulator 222 is configuredas a fan 236 (e.g., a blower fan) that is located within the lowerplenum 220 (e.g., within the ducting system 226). It is also envisioned,however, that the lower air circulator 222 may be located externally ofthe lower plenum 220. For example, the lower air circulator 222 may beconnected to (or otherwise supported on) an outer surface 238 of theducting system 226.

The lower heat sink 224 is connected to (e.g., located within) the lowerplenum 220 and is configured to treat the air circulated therethrough(e.g., alter the temperature of the air within the lower plenum 220 viacooling or heating) prior to direction across the power source 14 of theUAV 10. For example, when the temperature control system 200 is utilizedto cool the power source 14 of the UAV 10, the lower heat sink 224absorbs and distributes thermal energy (heat) from the air flowingthrough the lower plenum 220 to lower the temperature thereof and, thus,the power source 14 of the UAV 10. To increase the absorption anddistribution of thermal energy by the lower heat sink 224 and, thus,enhance cooling of the power source 14 of the UAV 10, air flow throughthe lower plenum 220 and, thus, air flow across the lower heat sink 224,may be increased by increasing the speed of the lower air circulator 222(e.g., by increasing power to the fan 236).

The TEC 206 is configured as a Peltier system and includes and adedicated/integrated power source/control as well as a first (upper,“hot”) end 240 (FIG. 51 ) and a second (lower, “cold”) end 242, each ofwhich includes a thermal member (e.g., a ceramic plate). The first end240 is thermally and/or physically connected to the upper heat sink 212and the second end 242 is thermally and/or physically connected to thelower heat sink 224. Upon activation, as current flows through the TEC206, the temperature of the first end 240 increases (to an uppertemperature threshold) while the temperature of the second end 242decreases (to a lower temperature threshold) until a predetermined,fixed temperature differential is realized. For example, it isenvisioned that the differential between the respective upper and lowerends 240, 242 of the TEC 206 may lie substantially within the range of(approximately) 30° C. to (approximately) 70° C. (e.g., (approximately)50° C.). Embodiments in which the temperature differential may lieoutside the disclosed range, however, are also envisioned herein andwould not be beyond the scope of the present disclosure. Consequently,reducing the upper temperature threshold allows for a correspondingreduction in the lower temperature threshold.

During operation of the temperature control system 200, in theparticular embodiment of the disclosure illustrated, thermal energy(heat) generated by the TEC 206 is absorbed and dissipated by the upperheat sink 212 and the ambient air flowing through the upper plenum 208.The upper air circuit 202 thus cools the first (“hot”) end 240 of theTEC 206, which results in corresponding cooling of the second (“cold”)end 242 of the TEC 206 and, thus, increased cooling of the air flowingthrough the lower plenum 220 and the power source 14 of the UAV 10 whenthe UAV 10 is docked in the base station 100.

Although illustrated as including a single TEC 206 in the particularembodiment shown throughout the figures, embodiments are also envisionedin which the temperature control system 200 may include multiple TECs206. In such embodiments, it is envisioned that the TECs 206 may beidentical or non-identical in configuration (e.g., it is envisioned thatthe temperature control system 200 may include TECs 206 that vary insize) and/or that the TECs 206 may be arranged in series or in parallel(e.g., in a stacked configuration).

As indicated above, embodiments of the disclosure are envisioned hereinin which the temperature control system 200 may be configured to heat,rather than cool, the power source 14 of the UAV 10 when the UAV 10 isdocked in the base station 100. In such embodiments, current flowthrough the TEC 206 can be reversed (e.g., via electronic control) suchthat the first end 240 of the TEC 206 functions as the “cold” end andthe second end 242 of the TEC 206 functions as the “hot” end.

During use of the temperature control system 200, the upper air circuit202 draws air in from the ambient, either from within the base station100 or externally of the base station 100, which is directed across theupper heat sink 212 via the upper air circulator 210. As the air flowsacross the upper heat sink 212, heat is withdrawn, thereby cooling theupper heat sink 212 and, thus, the first (“hot) end 240 of the TEC 206,and heating the air. The heated air is then discharged from the upperair circuit 202, being expelled either into the base station 100 orexternally thereof (e.g., through a vent), and is replaced by coolerambient air that is drawing into the upper air circuit 202 by the upperair circulator 210.

Upon docking of the UAV 10, as the cradle 106 moves from the extendedposition (FIG. 13 ) into the retracted position (FIGS. 2, 10 ), theforward section 230 of the lower plenum 220 mates with (engages) therear section 228, which closes the lower air circuit 204 and allows forthe continuous circulation of air therethrough. To facilitate matingengagement between the forward section 230 and the rear section 228, itis envisioned that the forward section 230 and the rear section 228 mayinclude one or more seals (e.g., O-rings) or corresponding engagementstructures (e.g., collars, flanges, or the like) at the interfacetherebetween.

Air flowing through the lower air circuit 204 is directed across thelower heat sink 224 via the lower air circulator 222, which withdrawsheat from the air to cool the air prior to entering the chamber 142 ofthe cradle 106 via the air inlet 232. As the cooled air flows throughacross the cradle 106 and through the chamber 142, heat is withdrawnfrom the power source 14 (FIGS. 2, 4, 5 ) of the docked UAV 10, which isfacilitated by the heat exchanger 24. More specifically, in theillustrated embodiment, the cooled air flows through the channels 32(FIG. 4 ) defined by the diffusers 26 (e.g., the fins 30), whichincreases the distribution of thermal energy from the power source 14 ofthe UAV 10 to enhance cooling, and increases the temperature of the air.After flowing across the power source 14, the (heated) air exits thechamber 142 via the air outlet 234 and is redirected across the lowerheat sink 224 (e.g., via the lower air circulator 222) to again cool theair prior to recirculation through the cradle 106 and across the powersource 14.

Cradle Insulation

With reference to FIGS. 56-58 , in certain embodiments of thedisclosure, it is envisioned that the cradle 106 may include aninsulated construction to allow for increased control over, andregulation of, the temperature of the power source 14 of the UAV 10 whenthe UAV 10 is docked within the base station 100. More specifically,insulation of the cradle 106 promotes and facilitates cooling andheating of the power source 14 and maintains the temperature of thepower source 14 for increased periods of time.

The (insulated) cradle 106 includes: an upper (first) shell 362; a lower(second) shell 364; and one or more thermal insulators 366, wherein theshells 362, 364 collectively define a housing 365 of the cradle 106. Itis envisioned that the shells 362, 364 and the thermal insulator(s) 366may be formed from any suitable materials. For example, in theparticular embodiment illustrated, the shells 362, 364 each include(e.g., are formed partially or entirely from) one or more non-metallic(e.g., plastic) materials and the thermal insulator(s) 366 include(e.g., are formed partially or entirely from) an insulative foam.Embodiments in which the shells 362, 364 and/or the thermal insulator(s)366 may include one or more alternate materials, however, would not bebeyond the scope of the present disclosure. For example, embodiments inwhich the shell 362 and/or the shell 364 may include a compositematerial (e.g., carbon fiber) are also envisioned herein (e.g., toincrease the overall strength and/or rigidity of the cradle 106).

The upper shell 362 is configured to receive the UAV 10 during dockingand defines the chamber 142, the sidewalls 146, the air inlet 232 (FIGS.47-49 ), the air outlet 234, and the angled guide surface 148 mentionedabove, which collectively facilitate proper seating of the UAV 10 withinthe cradle 106.

The lower shell 364 is connected to the upper shell 362 and providesstructural rigidity to the cradle 106. The lower shell 364 defines acharging window 368, which is located in the rear end 106 b of thecradle 106, as well as a pair of airflow openings 370, 372 that are inrespective communication with the air inlet 232 and the air outlet 234so as to facilitate the circulation of cooled and heated air through thecradle 106 following conditioning by the TEC 206. As described infurther detail below, the charging window 368 is configured to receivethe charging hub 143 (FIG. 10 ) such that the charging hub 143 isextendable into and through the cradle 106 during retraction of the UAV10 into the base station 100 to thereby facilitate connection of thecharging hub 143 to the power source 14 of the UAV 10. The airflowopenings 370, 372 are in communication with the air inlet 232 and theair outlet 234, respectively, and allow cooled and heated air to enterthe cradle 106 following condition by the TEC 206.

With reference to FIG. 58 in particular, the cradle 106 (e.g., theassembly of the cradle 106 and the forward section 230 of the lowerplenum 220) includes lead-ins 374, which are positioned adjacent to(e.g., about) the airflow openings 370, 372 and each define a chamfered(beveled, angled) end walls 376 that facilitates entry of the cradle 106into the base station 100 during retraction. For example, in the eventof misalignment with the window 113 (FIG. 2 ) and contact with theenclosure 102 (e.g., the forward frame 116), the lead-ins 374 redirectthe cradle 106 (and the forward section 230 of the lower plenum 220)laterally inward, thereby inhibiting (if not entirely preventing)jamming, damage to the cradle 106 and/or the forward section 230 of thelower plenum 220, damage to the enclosure 102, etc. The chamfered endwalls 376 also facilitate proper registration of the cradle 106 (and theforward section 230 of the lower plenum 220) and are configured for(mating) engagement (contact) with corresponding chamfered (beveled,angled) end walls 378 (FIG. 58 ) on the rear section 228 of the lowerplenum 220 such that, upon retraction of the cradle 106, the cradle 106(and the forward section 230 of the lower plenum 220) mates with therear section 228 of the lower plenum 220, thereby facilitating properair flow through the temperature control system 200 and the cradle 106to support thermal conditioning (e.g., heating and cooling) of the powersource 14 of the UAV 10. The end walls 376, 378 thus definecorresponding mating surfaces on the cradle 106 and the rear section 228of the lower plenum 220, respectively.

It is envisioned that the shells 362, 364 may be connected together inany suitable manner. For example, in the particular embodiment of thecradle 106 illustrated, the shells 362, 364 are connected via one ormore mechanical fasteners (e.g., screws, pins, bolts, clips, etc.),which extend through openings 380 in the shells 362, 364. It isenvisioned, however, that the shells 362, 364 may be configured forconnection in any suitable manner. For example, embodiments are alsoenvisioned in which the shells 362, 364 may be configured for engagementin a press-fit (interference fit) arrangement. Mechanically connectingthe shells 362, 364 simplifies assembly and disassembly of the cradle106 so as to facilitate repair of the cradle 106, replacement of any ofthe components thereof, etc.

The thermal insulator(s) 366 are located and secured between the shells362, 364 (e.g., such that the thermal insulator(s) 366 are locatedwithin the housing 365) and collectively define an airflow channel 382that extends about the chamber 142 and, thus, the power source 14 whenthe UAV 10 is docked within the cradle 106. In the particular embodimentof the disclosure illustrated, the cradle 106 is shown as including apair of thermal insulators 366 (e.g., an upper thermal insulator 366 iand a lower thermal insulator 366 ii), which facilitates and simplifiesthe manufacture and assembly of the cradle 106. Embodiments are alsoenvisioned, however, in which the cradle 106 may include a singlethermal insulator 366 that is unitary in construction (e.g., amonolithic thermal insulator 366 that is formed from a single piece of(insulative) material).

The thermal insulator(s) 366 define an internal compartment 367 that isconfigured to receive (accommodate) the upper shell 362 such that theupper shell 362 (e.g., the chamber 142) extends into the thermalinsulator(s) 366. More specifically, in the particular embodimentillustrated, the thermal insulators 366 i, 366 ii respectively includean opening 367 a and a recess 367 b that collectively define theinternal compartment 367 such that, upon assembly of the cradle 106, thechamber 142 extends through the opening 367 a and is received by(positioned within) the recess 367 b.

The airflow channel 382 is configured to receive, direct, and circulatethermally-conditioned air within (e.g., through, across) the cradle 106.In the particular embodiment illustrated, the airflow channel 382extends between thermal insulators 366 i, 366 ii and includes a (first)channel portion 384 with respective rear and front ends 386, 388 that isin communication with the airflow opening 370 and the air inlet 232 anda (second) channel portion 390 with respective rear and front ends 392,394 that is in communication with the airflow opening 370 and the airoutlet 234. As seen in FIG. 57 , the respective front ends 388, 392 ofthe channel portions 384, 390 are separated by a nose section 396 of thecradle 106. The airflow channel 382 thus includes a discontinuousconfiguration that partially circumscribes the cradle 106 and thechamber 142 and inhibits (if not entirely prevents) air flow from thefront end 388 of the channel portion 384 into the front end 394 of thechannel portion 390, thereby directing air from the air inlet 232,across the chamber 142, and into the air outlet 234. Embodiments inwhich the airflow channel 382 may include a continuous (uninterrupted)configuration that entirely circumscribes the cradle 106 and the chamber142 would not be beyond the scope of the present disclosure, however.

Weather and Climate Management

To allow for operation in various weather conditions, the base station100 includes a plurality of components and systems that are configuredto regulate temperature, moisture, humidity, and the like in order tomaximize operability in a variety of environments.

Snow and Ice

As seen in FIGS. 53A and 53B, in certain embodiments of the disclosure,the base station 100 includes a (primary) heating system 244 thatincludes one or more heating elements 244 a (e.g., resistive heaters 244b) that are thermally and/or physically connected to (supported by) theenclosure 102 (e.g., via an adhesive). Although shown as beingassociated with (supported by) the roof section 176 of the outer housing110 in the particular embodiment illustrated, it is envisioned that theheating element(s) 244 a may be thermally and/or physically connected toany section(s) of the outer housing 110 that may benefit from heating.Upon activation, the heating element(s) 244 a increase the temperatureof (heat) the outer housing 110 (e.g., to reduce the presence of snowand/or ice on the roof section 176 and thereby expose (reveal) thefiducial(s) 168 to facilitate visual identification of the base station100 and/or guidance of the UAV 10 during landing and docking with thebase station 100). To further assist with the management ofprecipitation (e.g., snow, ice, sleet, rain, etc.), it is envisionedthat the roof section 176 may be pitched (e.g., at 3°-5°) to encouragerunoff and inhibit (if not entirely prevent) pooling on the roof section176.

It is envisioned that the heating element(s) 244 a may be connected toany suitable power source, whether internal to the base station 100(e.g., to the power supply controlled by the main board/processor) orexternal (e.g., to a separate power supply, battery, or the like), andthat the heating system 244 (e.g., the heating element(s) 244 a) may beeither manually or automatically activated. For example, it isenvisioned that he heating system 244 may be activated via a signal thatis relayed by one or more temperature sensors 246 that are incommunication with the heating element(s) 244 a and which are configuredto detect a threshold (environmental) temperature such that the heatingsystem 244 is automatically activated when the temperature falls belowor exceeds a predetermined value (e.g., 32° F.). Additionally, oralternatively, it is envisioned that the heating system 244 may beactivated upon receiving an activation signal from a weather station(e.g., via a cloud-based or other such wireless connection) and/or fromthe visualization system 174, which may be configured to visuallyinspect environmental conditions (e.g., to detect the presence of snowand/or ice) and relay the activation signal to the heating system 244.

With reference to FIGS. 59-62 , to further support operation of the basestation 100 in cold environments and/or conditions, it is envisionedthat the base station 100 may include a (secondary) heating system 245that is supported by the enclosure 102. More specifically, the heatingsystem 245 includes one or more additional (interior) heating elements244 a that are supported by (connected to) an inner (internal) surface116 b of the forward frame 116 to facilitate opening and closure of thedoor 104. The heating system 245 is located (positioned) adjacent (orgenerally adjacent) to a sealing member 398, which is configured forengagement (contact) with the door 104 to form a seal therewith so as toinhibit (if not entirely prevent) the entry of dust, debris, moisture,water, etc., into the base station 100. More specifically, the sealingmember 398 is supported by the enclosure 102 (e.g., the forward frame116) and extends about the window 113. To augment the distribution ofthermal energy from the heating elements 244 a, in certain embodiments,it is envisioned that a thermal interface material 400 may be provided(located) between the forward frame 116 and the heating element(s) 244a, as seen in FIG. 61 .

As discussed above in connection with FIGS. 53 a, 53 b and heating ofthe roof section 176, the heating system 245 may be connected to anysuitable power source, whether internal or external to the base station100 and may be either manually or automatically activated (e.g., via asignal that is relayed by one or more temperature sensors 246, uponreceiving an activation signal from a weather station and/or from thevisualization system 174, etc.). Upon activation of the heatingelement(s) 244 a, thermal energy is communicated to the sealing member398 and/or the door 104 to heat the sealing member 398 and/or the door104. Heating of the sealing member 398 and/or the door 104 melts snow,ice, etc., and thereby facilitates proper opening and closure of thedoor 104.

In certain embodiments of the disclosure, it is envisioned that theheating system 245 may also include the status indicator(s) 172. In suchembodiments, the light source(s) 173 (e.g., the LED(s) 186) may serve toaugment the thermal effects of the heating element(s) 244 a by utilizingthe thermal conductivity of the sheet metal used comprising the outerhousing 110 (e.g., the forward frame 116) to communicate heat generatedvia operation of the status indicator(s) 172 to the sealing member 398and/or the door 104. In such embodiments of the disclosure, the statusindicator(s) 172 thus offer dual functionality (e.g., illumination andheating of the sealing member 398 and/or the door 104).

With reference to FIG. 63 , in certain embodiments of the disclosure,additionally or alternatively, it is envisioned that the sealing member398 and/or the door 104 may include one or more thermally conductivemembers 402 (e.g., strip heaters, wires, coils, plates, etc.), which maybe connected to any suitable power source, whether internal or externalto the base station 100. For example, in the particular embodimentillustrated, the base station 100 includes a (first) thermallyconductive member 402 i that is embedded within the sealing member 398and a (second) thermally conductive member 402 ii that is embeddedwithin the door 104. In such embodiments, upon activation of thethermally conductive members 402, electrical energy is communicated(transferred) to the sealing member 398 and/or the door 104 to therebyheat the sealing member 398 and/or the door 104 and effectuate thenecessary or desired temperature change.

Internal Temperature and Humidity Regulation

To regulate (control) the temperature and/or humidity within the basestation 100, it is envisioned that the base station 100 may include oneor more internal fans 248 (FIG. 64 ), which may be supported in anysuitable location on the inner housing 108 and/or the outer housing 110.The internal fan(s) 248 regulate (e.g., vary, control) temperatureand/or humidity within the base station 100 and may be configured toeither cool the base station 100 or heat the base station 100 (e.g., viathermal connection to one or more heating elements or components).

The internal fan(s) 248 are controllable (e.g., via the mainboard/processor) to draw air in and exhaust air through one or moreports/vents in the outer housing 110 and/or the inner housing 108, thelocation(s) of which may be varied to direct air flow in a particulardirection (e.g., across the UAV 10). For example, it is envisioned thatthe port(s)/vent(s) may be located and/or configured to create air flowthrough the base station 100 in any effective (or otherwise desired)pattern.

In certain embodiments of the disclosure, it is envisioned that theinternal fan(s) 248 may be automatically activated via a signal that isrelayed by one or more sensors 250 that are configured to detecttemperature, humidity, etc. Additionally, or alternatively, it isenvisioned that the internal fan(s) 248 may be connected to a timer suchthat the internal fan(s) 248 are automatically activated at a particulartime of day.

In the context of humidity regulation, upon the detection of moisture,the sensor(s) 250 may generate an activation signal that can be utilizedto initiate one or more mitigation processes. For example, it isenvisioned that the sensor(s) may be in communication with the internalfan(s) 248 such that the internal fan(s) 248 are engaged upon receipt ofthe activation signal from the sensor(s) 250 to remove (or otherwisemitigate) excess humidity within the base station 100, therebyinhibiting (if not entirely preventing) condensation that mightotherwise compromise the functionality of one or more components of theUAV 10 or the base station 100. For example, the presence ofcondensation may result in malfunction and/or damage to the electronicsmodules (e.g., the main board/processor) and/or “fogging” of thevisualization system 174. To further inhibit (if not entirely prevent)the presence of humidity, condensation, moisture, etc., in certainembodiments of the disclosure, it is envisioned that the electronicsmodules may be sealed within the base station 100. For example, theelectronics module, or the various components thereof (e.g., motordrivers, interface boards, lighting boards, etc.), may be sealed, eithercollectively (via hermetic sealing) or individually (e.g., via dipcoating).

Drainage

In certain embodiments of the disclosure, the enclosure 102 (e.g., theouter housing 110) may include one or more channels 252 (FIG. 65 ) thatare configured to collect and direct water away from any entry pointsinto the enclosure 102 in a manner that inhibits (if not entirelyprevents) entry into the base station 100 and/or away from anycomponents, whether electronic, mechanical, or otherwise, that may becompromised by the presence of moisture. For example, it is envisionedthat the channel(s) 252 may be configured to collect and direct wateraway from the interface with any power cables, any lockingmembers/mechanisms, the door 104 (FIG. 1 ), etc. While the enclosure 102is shown as including a single channel 252 that extends about a rearperiphery 254 of the outer housing 110 in the particular embodimentillustrated, it should be appreciated that the number of channels 252and/or the location of the channels 252 may be varied without departingfrom the present disclosure. For example, embodiments including one ormore additional channels 252 are also envisioned herein, as areembodiments in which the enclosure 102 may include one or more channels252 that extend about a front periphery 256 (FIG. 1 ) of the outerhousing 110, the roof section 176, etc.

In the particular embodiment of the base station 100 illustrated in FIG.65 , the channel 252 is defined by an (molded) insert 258 that isincorporated into the outer housing 110. It is envisioned, however, thatthe channel(s) 252 may be configured in any manner suitable for theintended purpose of collecting and/or directing water in the mannerdescribed herein. For example, embodiments are also envisioned in whichthe channel(s) 252 may be integrally (e.g., monolithically) formed withthe outer housing 110.

In certain embodiments of the disclosure, to further inhibit (if notentirely prevent) water penetration, it is envisioned that the enclosure102 may include one or more seals, gaskets, etc., that are associatedwith the channel(s) 252. For example, it is envisioned that such seals,gaskets, etc., may be positioned about the insert 258 and supported bythe inner housing 108 and/or the outer housing 110.

It should be appreciated that any of the aforementioned componentsand/or systems may be omitted in order to reduce the overall cost andcomplexity of the base station 100. For example, in hot (e.g., desert)climates, it is envisioned that the heating element(s) 244 a may beeliminated.

Visualization System

With reference now to FIG. 1 , the visualization system 174 includes adigital image capturing device 260 (e.g., a digital camera) or the like.It is envisioned that the visualization system 174 may be connected toany suitable power source, whether internal to the base station 100(e.g., to the power supply controlled by the main board/processor) orexternal (e.g., to a separate power supply, battery, or the like).

In the particular embodiment of the disclosure illustrated, thevisualization system 174 includes a single digital image capturingdevice 260 that is secured (connected, mounted) to, or otherwisesupported by, the forward frame 116 of the outer housing 110, whichsupports observation and visual analysis of the environment in which thebase station 100 is located as well as observation and visual analysisof the UAV 10 (FIG. 2 ) prior to takeoff, during takeoff, and duringlanding. It should be appreciated, however, that the number of digitalimage capturing devices 260 and/or the location of the digital imagecapturing device(s) 260 may be varied in alternate embodiments withoutdeparting from the present disclosure. For example, embodimentsincluding one or more additional digital image capturing devices 260 arealso envisioned herein.

During operation of the base station 100, the visualization system 174supports visual inspection of the environment, which not only improvessafety of the base station 100 and the UAV 10 by confirming the absenceof people, animals, etc., prior to takeoff, during takeoff, and duringlanding of the UAV 10, but functionality of the base station 100 aswell. For example, it is envisioned that the visualization system 174may be configured to identify precipitation (e.g., snow, ice, rain,etc.) and actuate (trigger) operation of the heating element(s) 244 a(FIGS. 53A, 53B), the internal fan(s) 248 (FIG. 64 ), or other suchsystems. It is also envisioned that the visualization system 174 may beutilized to inspect the UAV 10 (e.g., prior to takeoff and/or duringdocking) and identify any damage that may result in subsequentsuboptimal performance. Charging of the UAV

With reference now to FIGS. 66-75 , charging of the UAV 10 will bediscussed. As indicated above, upon docking with the base station 100,the UAV 10 and the power source 14 are received by the cradle 106, whichfacilitates alignment and engagement with the charging hub 143. Thecharging hub 143 is configured for electrical connection to any suitablepower source, whether internal to the base station 100 or external, andincludes: a base 404; an alignment bracket 406 that is movably(slidably) supported by the base 404; one or more biasing members 408; acharging member 410 including a PCB 412 and a (male) electricalconnector 414; and a cap (cover, lid) 416 that overlies the chargingmember 410.

The base 404 is fixedly (non-movably) connected to the enclosure 102 andsupports the remaining components of the charging hub 143. Morespecifically, in the particular embodiment illustrated, the base 404 isfixedly (non-movably) connected to the slide mechanism 150 (e.g., thestationary slide member 151 a), as seen in FIGS. 10 and 64 , forexample, by a plurality of mechanical fasteners 417 (FIG. 67 ) (e.g.,screws, pins, bolts, clips, etc.), which fixes the charging hub 143 inrelation to not only the enclosure 102, but the cradle 106 and the UAV10. It should be appreciated, however, that the particular location ofthe base 404 may be varied in alternate embodiments without departingfrom the scope of the present disclosure. For example, embodiments arealso envisioned in which the base 404 may be connected to the sheetmetal base 264 (FIG. 14 ) of the enclosure 102.

The base 404 defines a cavity (receptacle) 418 (FIG. 71A) that isconfigured to receive the alignment bracket 406 (and the biasingmember(s) 408) such that the alignment bracket 406 is movable within thecavity 418 and in relation to the base 404 during repositioning betweena normal (initial, extended) position (FIG. 71A) and a deflected(subsequent, retracted) position (FIG. 71B), as described in furtherdetail below. More specifically, the base 404 includes: a rear end wall420, which includes a boss (support) 422; a front end wall 424;sidewalls 426, 428; and a base wall 430, which collectively define thecavity 418.

The base wall 430 is configured to support the alignment bracket 406during repositioning between the normal and deflected positions. Thebase wall 430 extends between the side walls 426, 428 and includesopposing (rear and front) ends 434, 436 that are spaced from the endwalls 420, 424, respectively. More specifically, the ends 434, 436 ofthe base wall 430 are spaced (axially) from the end walls 420, 424 suchthat the base 404 defines (first, rear and second, front) openings 438,440, respectively. The opening 438 is configured to provide access tothe cavity 418 during manufacture and assembly of the charging hub 143(e.g., to facilitate fabrication of the base 404 and the alignmentbracket 406) and the opening 440 is configured to receive the alignmentbracket 406 such that the alignment bracket 406 is insertable into thebase 404 during assembly of the charging hub 143.

The base wall 430 defines a guide surface 442 (FIG. 73 ) that isconfigured for contact (engagement) with the alignment bracket 406during extension and retraction within the cavity 418. In order tofacilitate and support proper movement and repositioning of thealignment bracket 406, the (front) end 436 of the base wall 430 includesa chamfered (beveled) surface 444 that is configured for engagement(contact) with the alignment bracket 406 so as to direct the alignmentbracket 406 into contact (engagement) with the guide surface 442 andthereby inhibit jamming.

The alignment bracket 406 supports (and is connected to) the chargingmember 410 and facilitates proper alignment between the UAV 10 and thecharging hub 143 during retraction of the cradle 106 and, thus,electrical connection of the charging member 410 and the power source 14of the UAV 10. In the particular embodiment illustrated, the alignmentbracket 406 is unitary (e.g., monolithic) in construction and is formedfrom a single piece of material. In alternate embodiments of thedisclosure, however, it is envisioned that the alignment bracket 406 mayinclude a series of individual components that are connected together inany suitable manner (e.g., via one or more mechanical fasteners, in aninterference fit, etc.). As described in detail below, the alignmentbracket 406 includes: a head section 448; a body 450 that extends fromthe head section 448; and a leg 452 that extends from the body 450.

The head section 448 defines (first and second) platforms 454, 456 thatare configured to support the PCB 412 and the electrical connector 414,respectively, and includes one or more alignment members 458. Theplatform 454 defines an aperture 460 that is configured to receive amechanical fastener 462 (FIG. 72 ) (e.g., a screw, a pin, a bolt, aclip, etc.), which releasably and fixedly (non-movably) connects thecharging member 410 and the alignment bracket 406 such that the chargingmember 410 and the alignment bracket 406 are movable in unison(contemporaneously), along an axis of movement M, during repositioningof the alignment bracket 406 between the normal and deflected positions.

The alignment member(s) 458 extends axially forward of the chargingmember 410 (e.g., the electrical connector 414) along the axis ofmovement M and are configured for insertion into a receptacle 464defined by the power source 14 of the UAV 10 so as to facilitate properpositioning of the charging member 410 and electrical connection to theUAV 10, as described in further detail below. In the particularembodiment illustrated, the alignment bracket 406 includes a pair ofalignment members 458 i, 458 ii that are each configured as a pin 466.It should be appreciated, however, that the particular number and/orconfiguration of the alignment members 458 may be altered in variousembodiments without departing from the scope of the present disclosure.For example, an embodiment of the alignment bracket 406 including asingle alignment member 458 is also envisioned herein.

In order to improve tolerances, the alignment member 458 includes atapered (conical) end 468 and the receptacle 464 includes chamfered(beveled) mouth 470. The tapered end 468 of the alignment member 458 andthe chamfered mouth 470 of the receptacle 464 allow and account for anyoffset (misalignment) therebetween and thereby facilitate properinsertion of the alignment member 458 into the receptacle 464

The body 450 of the alignment bracket 406 extends rearwardly from thehead section 448 and defines a recess 472 (FIG. 71A), which extendsbetween the head section 448 and the leg 452. The recess 472 isconfigured to receive the end wall 424 (defining the cavity 418 in thebase 404) such that the end wall 424 spaced an axial distance D from thehead section 448 of the alignment member 458, which extends in parallel(or generally parallel) relation to the axis of movement M. Duringretraction of the alignment bracket 406 (e.g., as the UAV 10 isconnected to charging hub 143), the end wall 424 moves forwardly throughthe recess 472 (e.g., towards the head section 448 of the alignmentmember 458), and during extension of the alignment bracket 406 (e.g., asthe UAV 10 is disconnected from charging hub 143), the end wall 424moves rearwardly through the recess 472 (e.g., towards the leg 452). Therange of (maximum) relative motion between the alignment bracket 406 andthe base 404 is thus equivalent to (defined by) the distance D betweenthe end wall 424 of the base 404 and the head section 448 of thealignment member 458.

The leg 452 extends vertically upward from the body 450 of the alignmentbracket 406 in parallel (or generally parallel) relation to the headsection 448 and includes a boss (support) 474 and an anchor (foot) 476.The boss 474 extends rearwardly from the leg 452 (e.g., away from thehead section 448) and is (vertically) aligned (or generally aligned)with the boss 422 so as to facilitate engagement of (contact between)the bosses 422, 474 upon movement of the alignment member 458 into thedeflected position (FIG. 71B), whereby the bosses 422, 474 collectivelydefine a hard stop 477 that prevents overtravel of the alignment bracket406 and, thus, the charging member 410 and the electrical connector 414.In certain embodiments of the disclosure, it is also envisioned thatbosses 422, 474 may be formed and accessed through the opening 438 inthe base 404 (e.g., during injection molding) and that the bosses 422,474 may provide location features (reference points) to facilitateproper assembly of the charging hub 143.

As seen in FIG. 72 , the anchor 476 is configured for insertion into acorresponding opening 478 in the charging member 410 (e.g., the PCB412). Positioning of the anchor 476 within the opening 478 furtherfacilitates connection of the charging member 410 to the alignmentbracket 406 and inhibits (if not entirely prevents) relative movementtherebetween such that the charging member 410 moves concomitantly withthe alignment bracket 406 during retraction and extension.

In the particular embodiment illustrated in FIGS. 66-74 , the charginghub 143 includes a single biasing member 408 that is configured as acoil spring 480. It should be appreciated, however, that the particularnumber and/or configuration of the biasing member(s) 408 may be variedin alternate embodiments without departing from the scope of the presentdisclosure. For example, FIG. 75 illustrates an embodiment of thecharging hub 143 that includes a pair of biasing members 408.

The biasing member 408 is located within the cavity 418 and is capturedbetween the alignment bracket 406 and the base 404. More specifically,the biasing member 408 includes a first (rear) end 482 that engages(contacts) the base 404 and a second (front) end 484 that engages(contacts) the alignment bracket 406. More specifically, the first end482 of the biasing member 408 is supported by (connected to) the boss422 and the second end 484 of the biasing member 408 is supported by(connected to) the boss 474, whereby the biasing member 408 is(vertically) offset from the alignment member(s) 458 along a (vertical)axis V that extends in orthogonal (or generally orthogonal) relation tothe axis of movement M.

The charging hub 143 (e.g., the base 404 and the alignment bracket 406)is configured such that the biasing member 408 carries a preloadedforce, whereby the biasing member 408 sits in compression between thealignment bracket 406 and the base 404 (e.g., between the bosses 422,474). The preload carried by the biasing member 408 biases (urges) thealignment bracket 406 towards the normal position and increasesalignment between the charging member 410 and the power source 14 of theUAV 10 to facilitate proper electrical connection thereof.

The charging member 410 includes the PCB 412 and the electricalconnector 414 mentioned above and is configured for electricalconnection to the power source 14 of the UAV 10. The electricalconnector 414 is fixedly connected (e.g., soldered) to the PCB 412 so asto inhibit (if not entirely prevent) relative movement therebetween,whereby the electrical connector 414 moves concomitantly(simultaneously) with the PCB 412 and the alignment bracket 406 duringrepositioning of the alignment bracket 406 between the normal anddeflected positions. To allow for axial displacement (movement) of thePCB 412 and the electrical connector 414 during repositioning of thealignment bracket 406, the charging hub 143 includes an opening 486(FIGS. 67, 70, 71A) defined in a rear end 488 thereof. The opening 486is configured to receive the PCB 412 and the electrical connector 414and allows the PCB 412 and the electrical connector 414 to exit andre-enter the charging hub 143 (e.g., the base 404) during retraction andextension of the alignment bracket 406. As seen in FIG. 71A, forexample, the PCB 412 and the electrical connector 414 are configured andpositioned such that they are concealed by the charging hub 143 when thealignment bracket 406 is in the normal position.

Together, the PCB 412 and the electrical connector 414 establish andcontrol (regulate) electrical connection and communication between thecharging hub 143 and the power source 14 of the UAV 10. Morespecifically, the PCB 412 and the electrical connector 414 allow for thetransmission of data between the UAV 10 and the base station 100 (viathe charging hub 143) including, for example, the temperature of thepower source 14, the voltage in each of the power cell(s) 20 (FIG. 5 ),the occurrence of an undervoltage event, the number charge cycles,information pertaining to the general health and status of the powersource 14, etc.

The electrical connector 414 is configured for insertion into an opening490 on the power source 14 of the UAV 10 through the charging window 368(FIGS. 66, 67, 71A) defined in the rear end 106 b of the cradle 106. Thecharging window 368 is configured to receive the charging member 410such that the charging member 410 moves into and out of the cradle 106during repositioning of the slide mechanism 150 and the cradle 106between the extended and retracted positions. Upon insertion of thecharging member 410 through the charging window 368, the electricalconnector 414 engages a corresponding (female) electrical connector 492on the power source 14 so as to establish an electrical connectionbetween the base station 100 (e.g., the charging hub 143) and the UAV 10that facilitates charging of the power source 14.

In certain embodiments of the disclosure, it is envisioned that thecharging window 368 may be reconfigurable between an open position, inwhich the charging member 410 is receivable by the charging window 368,and a closed position, in which the charging window 368 is concealed, soas to inhibit (if not entirely prevent) unintended contact between theUAV 10 and the cradle 106 (e.g., abutment of the charging member 410with the walls defining the charging window 368). For example, it isenvisioned that the cradle 106 may include a movable door that isconfigured to expose the charging window 368 in the open position andconceal the charging window 368 in the closed position.

The cap 416 defines a channel 494 (FIGS. 67, 74 ) that is configured toreceive the charging member 410, which allows for movement of thecharging member 410 in relation to the cap 416 (and the base 404), asdescribed in further detail below. The cap is releasably connected tothe base 404 by a plurality of mechanical fasteners 496 (e.g., screws,pins, bolts, clips, etc.) (FIGS. 68, 74, 75 ). The cap 416 thus inhibits(if not entirely prevents) rotation (twisting) of the alignment bracket406 and the charging member 410 in relation to the base 404 that mayotherwise occur during insertion of the alignment member(s) 458 into thereceptacle 464 (e.g., during repositioning the alignment bracket fromthe normal position into the deflected position) as a result of thevertical offset between the alignment member(s) 458 and the biasingmember 408.

During connection of the UAV 10 to the charging hub 143, it isenvisioned that misalignment may occur between the charging member 410and the power source 14 of the UAV 10. For example, misalignment mayoccur as a result of variability in seating of the UAV 10 within thecradle 106, exchange (replacement) of the power source 14, which mayresult in seating of the UAV 10 in a different position within thecradle 106, etc. Any such misalignment, however, is accommodated byaxial, vertical, and horizontal tolerances (gapping), which allows formovement of the alignment bracket 406 and the charging member 410 inrelation to the base 404 and the cap 416 in three degrees of freedom.More specifically, axial movement (floating, displacement) of thecharging member 410 along the axis of movement M (FIG. 71A) is toleratedvia repositioning of the alignment bracket 406 (and the charging member410) between the normal position (FIG. 71A) and the deflected position(FIG. 71B), which is facilitated by the cavity 418 in the base 404 andthe axial separation between the end wall 424 and the head section 448of the alignment bracket 406. Additionally, the charging hub 143 isconfigured so as to define vertical gaps G1, G2 (FIG. 71A) between thebase 404, the charging member 410, and the cap 416, which allow formovement (floating, displacement) of the charging member 410 along thevertical axis V as well as (lateral) horizontal gaps G3, G4 (FIG. 67 )between the charging member 410 and the cap 416, which is facilitated bythe relative dimensioning of the charging member 410 and the channel494. The gaps G3, G4 allow for movement (floating, displacement) of thecharging member 410 within the channel 494 along a horizontal axis H,which extends in orthogonal (or generally orthogonal) relation to theaxis of movement M and the vertical axis V (FIG. 71A).

The axial, vertical, and horizontal tolerances described above not onlyfacilitate more robust, consistent connection of the UAV 10 and thecharging hub 143, but protects the UAV 10, the charging hub 143, and thebase station 100 during retraction of the cradle 106 and the UAV 10. Forexample, in instances of gross misalignment (e.g., when connection ofthe charging member 410 to the power source 14 is physicallyimpossible), retraction of the alignment bracket 406 and the chargingmember 410 inhibits (if not entirely prevents) damage to the UAV 10, thecharging member 410, etc. (e.g., puncturing of the UAV 10, unseating ofthe UAV 10 from the cradle 106, etc.).

With continued reference to FIGS. 66-74 , a method of using the basestation 100 to charge the UAV 10 (e.g., the power source 14) will bediscussed. Initially, the UAV 10 is docked within the cradle 106, duringwhich, the power source 14 is guided into the chamber 142 (FIG. 67 ) bythe sidewalls 146 and the angled guide surface 148. After docking withthe cradle 106, the cradle 106 is retracted into the enclosure 102 viarepositioning of the slide mechanism 150 from the extended position intothe retracted position, during which, the charging hub 143 is insertedinto the cradle 106. More specifically, as the slide mechanism 150 (andthe cradle 106) moves into the retracted position, the alignment bracket406 is inserted into the receptacle 464 defined by the power source 14of the UAV 10, as seen in FIG. 71A, which facilitates proper positioningof the charging member 410 and alignment of the electrical connector 414with the opening 490 on the power source 14. Continued retraction of thecradle 106 causes insertion of the charging member 410 into the powersource 14 (via the opening 490) and, thus, engagement (contact) betweenthe electrical connectors 414, 492 so as to establish an electricalconnection between the power source 14 and the charging hub 143.

During retraction of the cradle 106, biasing of the alignment bracket406 towards the normal position (FIG. 71A) supports a proper electricalinterface between the electrical connectors 414, 492. Additionally, theaxial tolerance created by the configuration of the base 404 and thealignment bracket 406 and the inclusion of the biasing member 408 allowsfor repositioning of the alignment bracket 406 between the normalposition (FIG. 71A) and the deflected position (FIG. 71B) as necessaryso as to accommodate misalignment between the UAV 10 and the charginghub 143, during which, the biasing member 408 is compressed, whichincreases the preloaded force carried by the biasing member 408.

Serviceability of Electronic Modules

With reference now to FIGS. 76-88 , the base station 100 includes aplurality of electronic modules that are configured to control certainfunctional aspects of the base station 100. More specifically, in theparticular embodiment of the disclosure illustrated, the base station100 includes a (first) electronics module 500; a (second) electronicsmodule 502; and a third electronics module 504. As described in furtherdetail below, each of the electronics modules 500, 502, 504 isspecifically configured and positioned for individual connection to anddisconnection from the base station 100, which allows each of theelectronics modules 500, 502, 504 to be removed separately (e.g., forrepair, service, replacement, etc.), thereby reducing downtime of thebase station 100.

The electronics module 500 is supported by the enclosure 102 and ishoused behind (inwardly of) a rear door 115 of the base station 100,which represents an alternate embodiment of the aforementioned accesspanel 114 (FIG. 7 ) and is hingedly connected to the rear end 102 b ofthe enclosure 102 such that the rear door 115 is repositionable betweena closed position (FIG. 76 ) and an open position (FIG. 83 ). Morespecifically, the electronics module 500 is removably connected to arear frame 506 of the outer housing 110 and is positioned adjacent tothe (rear) door 115 within an access window 508 defined by the rearframe 506. In the particular embodiment illustrated, the electronicsmodule 500 is secured (connected) to the rear frame 506 by a pluralityof mechanical fasteners 510 (FIG. 78 ) (e.g., screws, pins, bolts,clips, etc.) and is positioned in a (rear) upper corner section 512 ofthe base station 100 (e.g., to increase ease of access to theelectronics module 500 during connection and disconnection). It shouldbe appreciated, however, that the particular location of the electronicsmodule 500 may be altered in various embodiments without departing fromthe scope of the present disclosure, so long as access to theelectronics module 500 in the manner described herein is maintained. Forexample, embodiments are envisioned in which the electronics module 500may be connected to the rear frame 506 in a lower corner section 514 ofthe base station 100. With reference to FIG. 78 in particular, theelectronics module 500 includes: a main (first) heat sink 516; anauxiliary (second, supplemental, ancillary) heat sink 518; a logic board520; a (first) PCBA 522; an interface member 524; and an SD card 526, asdescribed in detail below.

The main heat sink 516 includes (e.g., is formed partially or entirelyfrom) a thermally conductive material (e.g., aluminum) and facilitatesthe distribution of thermal energy, either away from the electronicsmodule 500 (e.g., in hot environments and/or conditions) or towards theelectronics module 500 (e.g., in cold environments and/or conditions).The main heat sink 516 includes a body 528 with a block-styleconfiguration, which provides structural integrity to the electronicsmodule 500 to increase the stability (e.g., rigidity) thereof. The mainheat sink 516 thus acts as (and provides) a (first) housing component530 of the electronics module 500.

The body 528 of the main heat sink 516 defines a cavity (pocket) 532that includes one or more recesses 534 and one or more standoffs(bosses) 536. The cavity 532 is configured to receive (accommodate,house) the logic board 520 such that the logic board 520 is positionedin engagement (contact) with the standoff(s) 536.

The auxiliary heat sink 518 is connected to the main heat sink 516 andacts as (and provides) a (second) housing component 538 of theelectronics module 500 that supplements the distribution of thermalenergy performed by the main heat sink 516. More specifically, in theparticular embodiment illustrated, the heat sinks 516, 518 are connectedby a plurality of mechanical fasteners 540 (e.g., screws, pins, bolts,clips, etc.), which allows for assembly and disassembly of theelectronics module 500 during repair, service, replacement, etc. As seenin FIG. 77 , upon connection of the heat sinks 516, 518, the main heatsink 516 defines a plurality of side walls 542 that collectivelydescribe a perimeter 544 of the electronics module 500 and the auxiliaryheat sink 518 defines a (first, front) end wall 546 of the electronicsmodule 500.

Like the main heat sink 516, the auxiliary heat sink 518 includes (e.g.,is formed partially or entirely from) a thermally conductive material(e.g., aluminum) and facilitates the distribution of thermal energy,either away from the electronics module 500 (e.g., in hot environmentsand/or conditions) or towards the electronics module 500 (e.g., in coldenvironments and/or conditions). While the heat sinks 516, 518 areillustrated as including identical materials of construction in theparticular embodiment shown, the present disclosure also envisionsembodiments in which the heat sinks 516, 518 may include differentmaterials of construction. For example, it is envisioned that the mainheat sink 516 may include (e.g., may be formed partially or entirelyfrom) a first material with a first thermal conductivity and that theauxiliary heat sink 518 may include (e.g., may be formed partially orentirely from) a second, different material with a second, differentthermal conductivity, which may be greater than or less than the firstthermal conductivity.

To increase the available surface area and, thus, the ability of theauxiliary heat sink 518 to distribute thermal energy, in certainembodiments, such as that which is illustrated, the auxiliary heat sink518 includes one or more diffusers 548, which may be configured in anymanner suitable for that intended purpose. For example, in theparticular embodiment illustrated, the diffusers 548 are configured asfins 550 that define a plurality of channels 552 therebetween, whichcollectively direct air flow along the auxiliary heat sink 518 tofurther increase the distribution of thermal energy. It should beappreciated, however, is envisioned that the diffuser(s) 548 may includeany suitable configuration (e.g., pins, protrusions, ribs, or other suchsurface irregularities) without departing from the scope of the presentdisclosure.

The logic board 520 supports operation and certain functional aspects ofthe base station 100 including, for example, temperature control of thepower source 14, powering of the heating elements(s) 244 a, powering ofthe light source(s) 173, 182, opening and closure of the (front) door104, extension and retraction of the slide mechanism 150 and the cradle106, communication between the base station 100, the UAV 10, and/or anexternal network, etc. As indicated above, the logic board 520 issupported by the main heat sink 516 (e.g., within the cavity 532),whereby the logic board 520 is located between, and is protected by, theheat sinks 516, 518. In certain embodiments of the disclosure, it isenvisioned that the cavity 532 (e.g., the recess(es) 534) may include athermal interface material (e.g., to augment the distribution of thermalenergy from the logic board 520 to the main heat sink 516).

The (first) PCBA 522 is supported by (connected to) the main heat sink516 so as to define a (second, rear) end wall 553 of the electronicsmodule 500. The PCBA 522 is configured to further support operation andcertain functional aspects of the base station 100 including, forexample, temperature control of the power source 14, powering of theheating elements(s) 244 a, powering of the light source(s) 173, 182,opening and closure of the (front) door 104, extension and retraction ofthe slide mechanism 150 and the cradle 106, etc. To support suchoperation and functionality, the PCBA 522 includes a processor 554 thatis configured to facilitate data processing and control of the basestation 100.

In certain embodiments, it is envisioned that the PCBA 522 may also beconnected to one or more of the antennas on the base station 100 (e.g.,the antenna(s) 166) via one or more antenna ports 556 (FIG. 78 ). It isenvisioned that connection of the PCBA 522 to the antenna(s) 166 mayallow for communication over WiFi, LTE, over various frequencies, etc.Although shown as including two antenna ports 556 in the particularembodiment illustrated, it should be appreciated that the particularnumber of antenna ports 556 may be varied without departing from thescope of the present disclosure.

The interface member 524 physically, thermally, and electricallyconnects the PCBA 522 and the heat sink 516 and is located therebetween.As seen in FIG. 78 , the interface member includes at least onethermally conductive section 558 and at least one electricallyconductive section 560. The thermally conductive section(s) 558 includea thermal interface material 562 and physically and thermally connectsthe PCBA 522 to the main heat sink 516 to facilitate the transfer ofthermal energy therebetween. The electrically conductive section(s) 560include an electrically conductive pressure-sensitive adhesive 564(e.g., to facilitate connection of the PCBA 522 to the main heat sink516) and are configured to electrically ground the various components ofthe PCBA 522 so as to facilitate and increase shielding fromelectromagnetic interference (EMI) and/or radiofrequency interference(RFI).

The SD card 526 is configured to further support operation and certainfunctional aspects of the base station 100 by facilitating high-capacitymemory and the reading and writing of a data to support processing(e.g., by the PCBA 522). Although illustrated as being supported by(connected to) the logic board 520 in the particular embodimentillustrated, it should be appreciated that the particular location ofthe SD card 526 may be varied in alternate embodiments without departingfrom the scope of the present disclosure. For example, embodiments inwhich the SD card 526 may be supported by (connected to) the PCBA 522are also envisioned herein.

With reference now to FIGS. 79 and 82 , in certain embodiments, the basestation 100 may further include an air circulation module 566 to furtherfacilitate the transfer of thermal energy away from, and thereby cool,the electronics module 500. As seen in FIG. 79 , the air circulationmodule 566 is positioned about the electronics module 500 and includesducting 568, which is configured to direct air flow across theelectronics module 500, and a (first) fan 570, which is supported by(connected to) the ducting 568 and is configured to draw airtherethrough.

The air circulation module 566 is removably supported by the enclosure102 adjacent to the (rear) door 115. More specifically, the aircirculation module 566 is connected to the rear frame 506 by a pluralityof mechanical fasteners 572 (FIG. 82 ) (e.g., screws, pins, bolts,clips, etc.), which allows for removal of the electronics module 500 andthe air circulation module 566 from the base station 100 independentlyof (separately from) each other to facilitate repair, service,replacement, etc., thereby further reducing downtime of the base station100. Whereas the electronics module 500 is supported by (connected to)an outer (rear) surface 574 of the rear frame 506, the air circulationmodule 566 is supported by (connected to) an inner (front) surface 576of the rear frame 506, whereby the rear frame 506 is located between theelectronics module 500 and the air circulation module 566.

As seen in FIG. 79 , the ducting 568 is configured to cover (overlie)the electronics module 500 and is configured in correspondence with theauxiliary heat sink 518. More specifically, the ducting 568 defines achamber 578 with an inner contour 580 that mirrors (e.g., substantiallymatches) an outer contour 582 defined by the diffuser(s) 548. Thecorresponding configurations of the ducting 568 and the diffuser(s) 548not only facilitates reception of the diffuser(s) 548 by the chamber578, but proper mating of the ducting 568 and the auxiliary heat sink518 as well as proper relative orientation of the air circulation module566 and the electronics module 500.

As indicated above, the electronics module 500 is positioned behind the(rear) door 115 within the access window 508 defined by the rear frame506 (e.g., such that the door 115 is positioned adjacent (or generallyadjacent) to the electronics module 500). The door 115 acts not only theprotect the electronics module 500, but reduce (if not entirelyeliminate) emissions from the base station 100. More specifically,together with the enclosure 102, the door 115 defines a Faraday cage forthe electronics module 500 that reduces (if not entirely eliminates) EMIand/or RFI. The door 115 also conceals and protects an air filterhousing 584 (FIG. 80 ) for one or more of the internal fans (e.g., thefan 248 (FIG. 64 )) located within the base station 100.

With reference to FIGS. 83 and 84 , the door 115 includes: a(non-metallic) frame 586; a (metallic) panel 588 that is supported by(connected to) the frame 586; a sealing member 590 that extends aboutthe panel 588 and which is configured for engagement (contact) with theenclosure 102 (e.g., the rear frame 506) to inhibit (if not entirelyprevent) the entry of dust, debris, moisture, water, etc., into the basestation 100; a plurality of hinges 592, which pivotably connect the door115 to the rear frame 506; and a locking mechanism 594, which inhibitstheft and/or unauthorized access to the internal components of the basestation 100 through the door 115. The multi-material construction of thedoor 115 (e.g., the use of both metallic and non-metallic materials) notonly reduces the overall weight of the door 115 and, thus, the basestation 100, but the overall cost of the base station 100.

The panel 588 is fixedly connected to the frame 586 by a plurality ofmechanical fasteners 596 (e.g., screws, pins, bolts, clips, etc.) suchthat the panel 588 is positioned in correspondence with the electronicsassembly 500 and covers (overlies) the electronics assembly 500 uponclosure of the door 115. The metallic construction of the panel 588results in the creation of an enclosed, metallic environment for theelectronics assembly 500 when the door 115 is closed and establishmentof the aforementioned Faraday cage upon grounding of the enclosure 102(e.g., the rear frame 506).

While the frame 586 and the panel 588 are respectively illustrated asincluding (e.g., as being formed partially or entirely from) plastic andsheet metal in the particular embodiment shown in the figures, it shouldbe appreciated that the particular material(s) used in construction ofthe frame 586 and the panel 588 may be varied without departing from thescope of the present disclosure.

With reference now to FIGS. 85-87 , the (second) electronics module 502will be discussed. The electronics module 502 is configured tofacilitate and control operation of the actuator(s) 118 and, thus,opening and closure of the (front) door 104. The electronics module 502is removably connected to a roof section 598 of the inner housing 108and includes: an access panel 600, which is removably supported by(connected to) the roof section 598; a (second) PCBA 602; and a (second)fan 604, each of which is secured (connected) to the access panel 600.

As seen in FIG. 87 , the access panel 600 is removably connected to aninner surface 606 of the roof section 598 via a plurality of mechanicalfasteners 608, whereby the electronics module 502 can be accessed and/orremoved from within the enclosure 102. Alternatively, the electronicsmodule 502 (e.g., the PCBA 602 or the fan 604) can be accessed (e.g.,serviced) externally upon removal of the outer housing 110 (FIG. 1 ). Inthe particular embodiment illustrated, the mechanical fasteners 608 areconfigured as thumb screws 610, which allow for toolless (e.g., manual)connection and disconnection of the access panel 600.

With reference now to FIG. 88 , the (third) electronics module 504 willbe discussed. The electronics module 504 is supported by (connected to)the slide mechanism 150 and is configured to facilitate and control theoperation thereof and, thus, repositioning of the cradle 106 between theretracted and extended positions. More specifically, the electronicsmodule 504 includes a (third) PCBA 612 that is removably connected tothe stationary slide member 151 b via a plurality of mechanicalfasteners 614, which allows the electronics module 504 to be accessedand removed from within the internal cavity 112 of the enclosure 102(via the front end 102 a) upon opening of the door 104 and removal ofthe UAV 10.

While the present disclosure has been described in connection withcertain embodiments, it is to be understood that the present disclosureis not to be limited to the disclosed embodiments, but, on the contrary,is intended to cover various modifications and equivalent arrangementsincluded within the scope of the appended claims, which scope is to beaccorded the broadest interpretation so as to encompass all suchmodifications and equivalent structures as is permitted under the law.

Persons skilled in the art will understand that the various embodimentsof the present disclosure and shown in the accompanying figuresconstitute non-limiting examples, and that additional components andfeatures may be added to any of the embodiments discussed hereinabovewithout departing from the scope of the present disclosure.Additionally, persons skilled in the art will understand that theelements and features shown or described in connection with oneembodiment may be combined with those of another embodiment withoutdeparting from the scope of the present disclosure to achieve anydesired result and will appreciate further features and advantages ofthe presently disclosed subject matter based on the descriptionprovided. Variations, combinations, and/or modifications to any of theembodiments and/or features of the embodiments described herein that arewithin the abilities of a person having ordinary skill in the art arealso within the scope of the present disclosure, as are alternativeembodiments that may result from combining, integrating, and/or omittingfeatures from any of the disclosed embodiments.

Use of the term “optionally” with respect to any element of a claimmeans that the element may be included or omitted, with bothalternatives being within the scope of the claim. Additionally, use ofbroader terms such as “comprises,” “includes,” and “having” should beunderstood to provide support for narrower terms such as “consistingof,” “consisting essentially of,” and “comprised substantially of.”Accordingly, the scope of protection is not limited by the descriptionset out above, but is defined by the claims that follow, and includesall equivalents of the subject matter of the claims.

In the preceding description, reference may be made to the spatialrelationship between the various structures illustrated in theaccompanying drawings, and to the spatial orientation of the structures.However, as will be recognized by those skilled in the art after acomplete reading of this disclosure, the structures described herein maybe positioned and oriented in any manner suitable for their intendedpurpose. Thus, the use of terms such as “above,” “below,” “upper,”“lower,” “inner,” “outer,” “left,” “right,” “upward,” “downward,”“inward,” “outward,” “horizontal,” “vertical,” etc., should beunderstood to describe a relative relationship between the structuresand/or a spatial orientation of the structures. Those skilled in the artwill also recognize that the use of such terms may be provided in thecontext of the illustrations provided by the corresponding figure(s).

Additionally, terms such as “approximately,” “generally,”“substantially,” and the like should be understood to allow forvariations in any numerical range or concept with which they areassociated and encompass variations on the order of 25% (e.g., to allowfor manufacturing tolerances and/or deviations in design). For example,the term “generally parallel” should be understood as referring toconfigurations in with the pertinent components are oriented so as todefine an angle therebetween that is equal to 180°±25% (e.g., an anglethat lies within the range of (approximately) 135° to (approximately)225°). The term “generally parallel” should thus be understood asreferring to encompass configurations in which the pertinent componentsare arranged in parallel relation.

Although terms such as “first,” “second,” “third,” etc., may be usedherein to describe various operations, elements, components, regions,and/or sections, these operations, elements, components, regions, and/orsections should not be limited by the use of these terms in that theseterms are used to distinguish one operation, element, component, region,or section from another. Thus, unless expressly stated otherwise, afirst operation, element, component, region, or section could be termeda second operation, element, component, region, or section withoutdeparting from the scope of the present disclosure.

Each and every claim is incorporated as further disclosure into thespecification and represents embodiments of the present disclosure.Also, the phrases “at least one of A, B, and C” and “A and/or B and/orC” should each be interpreted to include only A, only B, only C, or anycombination of A, B, and C.

What is claimed is:
 1. A base station for an unmanned aerial vehicle(UAV), the base station comprising: an enclosure defining a windowconfigured to receive the UAV to allow for entry of the UAV into thebase station and exit of the UAV from the base station; a door movablyconnected to the enclosure such that the door is repositionable betweena closed position and an open position; a sealing member extending aboutthe window and configured for engagement with the door so as to form aseal therewith when the door is in the closed position; and a heatingsystem supported by the enclosure and configured to heat the door and/orthe sealing member to support operation of the door in a coldenvironment, the heating system including: at least one light source;and at least one heating element.
 2. The base station of claim 1,wherein the at least one light source is configured to identify a statusof the base station.
 3. The base station of claim 1, wherein the atleast one light source is supported on an outer surface of the enclosureand the at least one heating element is supported on an inner surface ofthe enclosure.
 4. The base station of claim 1, further comprising athermal interface material located between the enclosure and the atleast one heating element.
 5. The base station of claim 1, wherein theheating system further includes at least one temperature sensorsupported by the enclosure.
 6. The base station of claim 1, wherein thedoor includes a thermally conductive member to further facilitateheating of the door.
 7. The base station of claim 6, wherein thethermally conductive member is embedded within the door.
 8. The basestation of claim 1, wherein the sealing member includes a thermallyconductive member to further facilitate heating of the sealing member.9. The base station of claim 8, wherein the thermally conductive memberis embedded within the sealing member.
 10. The base station of claim 9,further comprising at least one additional heating element supported bya roof section of the enclosure.
 11. Abase station for an unmannedaerial vehicle (UAV), the base station comprising: an enclosureconfigured to receive the UAV; a door movably connected to the enclosuresuch that the door is repositionable between a closed position and anopen position; a primary heating system associated with a roof sectionof the enclosure; and a secondary heating system associated with thedoor.
 12. The base station of claim 11, wherein the secondary heatingsystem includes: an exterior light source; and an interior heatingelement.
 13. The base station of claim 11, wherein the primary heatingsystem and/or the secondary heating system are configured for automaticactivation upon receiving an activation signal.
 14. The base station ofclaim 13, wherein the base station further includes a temperature sensorconfigured to relay the activation signal to the primary heating systemand/or the secondary heating system upon detecting a thresholdtemperature.
 15. The base station of claim 13, wherein the base stationfurther includes a visualization system supported by the enclosure andconfigured to visually inspect environmental conditions, thevisualization system configured to relay the activation signal to theprimary heating system and/or the secondary heating system.
 16. A methodof heating a base station for an unmanned aerial vehicle (UAV), themethod comprising activating a primary heating system associated with aroof section of the base station to expose at least one fiducialsupported by the roof section and thereby facilitate visualidentification of the base station by the UAV and/or guidance of the UAVduring landing and docking with the base station.
 17. The method ofclaim 16, further comprising activating a secondary heating systemassociated with a door of the base station to facilitate opening andclosure thereof.
 18. The method of claim 17, wherein activating thesecondary heating system includes activating at least one thermallyconductive member, wherein the at least one thermally conductive memberis connected to the door and/or a sealing member configured forengagement with the door.
 19. The method of claim 17, wherein activatingthe secondary heating system includes: activating an exterior lightsource; and activating an interior heating element.
 20. The method ofclaim 17, wherein activating the primary heating system and activatingthe secondary heating system includes automatically activating theprimary heating system and automatically activating the secondaryheating system upon receiving an activation signal from at least one of:a temperature sensor on the base station configured to detect athreshold temperature; a visualization system on the base stationconfigured to visually inspect environmental conditions; and a weatherstation wirelessly connected to the base station.